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Matthias Nott
2 days ago eb62fc6c4c21fa4436dcf1283daa2be4e34d6f6f 
 SPL Exam Questions EN/80 - Principles of Flight.md
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2020 In steady (stationary) gliding flight, there is no thrust, so only two forces act: gravity (weight) and the total aerodynamic force (the vector sum of lift and drag). For the glider to be in equilibrium, these two must be equal and opposite — meaning the resultant air force exactly compensates gravity. Lift and drag are merely components of this single aerodynamic resultant; neither lift alone nor drag alone balances weight.
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2226 ### Q2: What happens to the minimum flying speed when flaps are extended, thereby increasing wing camber? ^t80q2
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2428 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q2) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q2)
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4448 - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
4549 - **VS** = Stall Speed
4650 - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
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+- Examen Blanc: [VV Q30 p.217](Questionnaire%20toutes%20branches%20VV.pdf#page=217) (score: 0.24)
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+- PDF Answer: D
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4757 ### Q3: After one wing stalls and the nose drops, what is the correct technique to prevent a spin? ^t80q3
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4959 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q3) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q3)
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6474 #### Key Terms
6575 
6676 AoA = Angle of Attack
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6781 ### Q4: Which component is responsible for pitch stabilisation during cruise? ^t80q4
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6983 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q4) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q4)
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86100 #### Key Terms
87101 
88102 AoA = Angle of Attack
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89107 ### Q5: What can happen when the never-exceed speed (VNE) is surpassed in flight? ^t80q5
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91109 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q5) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q5)
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106124 #### Key Terms
107125 
108126 VNE = Never Exceed Speed
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109131 ### Q6: What effect does a rearward centre of gravity position have on a glider's handling? ^t80q6
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111133 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q6) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q6)
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126148 #### Key Terms
127149 
128150 CG = Centre of Gravity
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+- Examen Blanc: [VV Q52 p.64](Questionnaire%20toutes%20branches%20VV.pdf#page=64) (score: 0.23)
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+- PDF Answer: D
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129157 ### Q7: What purpose does the vertical tail fin (rudder assembly) serve? ^t80q7
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131159 ![](figures/Anatomy_sailplane_EN.png)
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144172 #### Explanation
145173 
146174 The vertical tail fin (fin + rudder) provides yaw stability and yaw control. The fixed fin acts as a weathervane that generates a restoring yaw moment if the aircraft sideslips. The movable rudder allows the pilot to command deliberate yaw inputs for coordination, crosswind correction, or spin recovery. The horizontal stabiliser handles pitch; wing dihedral handles roll stability; the vertical tail does not generate lift in the conventional sense.
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+- Examen Blanc: [VV Q52 p.222](Questionnaire%20toutes%20branches%20VV.pdf#page=222) (score: 0.25)
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+- PDF Answer: D
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148182 ### Q8: In a coordinated level turn at 60 degrees of bank, the load factor is approximately ^t80q8
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165199 #### Key Terms
166200 
167201 n — Load Factor (ratio of lift to weight: n = L/W)
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168206 ### Q9: What is the relationship between aspect ratio and induced drag? ^t80q9
169207 
170208 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q9) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q9)
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188226 - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
189227 - **AR** — Aspect Ratio — ratio of wingspan² to wing area
190228 - **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution)
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191233 ### Q10: When the elevator trim tab is deflected downward, what is the resulting pitch tendency? ^t80q10
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193235 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q10) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q10)
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205247 
206248 A downward-deflected trim tab produces an upward aerodynamic force on the trailing edge of the elevator, pushing the elevator's trailing edge up and its leading edge down — this effectively deflects the elevator downward, creating a nose-up pitching moment. Trim tabs work by aerodynamic force to relieve the pilot of sustained stick forces; their deflection is opposite to the desired elevator deflection.
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208254 ### Q11: What does the polar curve of a glider depict? ^t80q11
209255 
210256 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q11) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q11)
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225271 #### Key Terms
226272 
227273 m — mass of the aircraft
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+- Examen Blanc: [S1S Q16 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.27)
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+- PDF Answer: C
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228280 ### Q12: In straight and level flight, what happens to the required angle of attack as speed increases? ^t80q12
229281 
230282 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q12) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q12)
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249301 - **CL** = Lift Coefficient
250302 - **ρ** (rho) — air density
251303 - **S** — Wing Area — total planform area of the wings
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+- Examen Blanc: [VV Q21 p.184](Questionnaire%20toutes%20branches%20VV.pdf#page=184) (score: 0.23)
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+- PDF Answer: B
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252310 ### Q13: What is the function of wing fences or boundary layer fences? ^t80q13
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254312 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q13) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q13)
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267325 Wing fences are thin vertical plates on the upper surface of a swept or tapered wing that prevent the boundary layer from flowing spanwise (outward toward the tips). Without fences, the boundary layer migrates outward due to the pressure gradient, thickening at the tips and promoting tip stall. Fences confine the boundary layer to its local region, improving tip stall characteristics and aileron effectiveness at high angles of attack.
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269331 ### Q14: What happens to total drag at the speed for best glide ratio? ^t80q14
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271333 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q14) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q14)
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283345 
284346 The best glide ratio (maximum L/D) occurs at the speed where total drag is minimum. At this point, induced drag exactly equals parasite drag — any faster increases parasite drag more than induced drag decreases, and any slower increases induced drag more than parasite drag decreases. For a glider, this speed gives the flattest glide angle and the greatest distance per unit of altitude lost in still air.
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286352 ### Q15: What structural feature contributes to lateral (roll) stability in a glider? ^t80q15
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288354 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q15) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q15)
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300366 
301367 Wing dihedral — the upward V-angle of the wings — is the primary design feature providing lateral (roll) stability. When a gust or disturbance causes one wing to drop, the dihedral geometry increases the angle of attack on the lower wing, generating more lift and creating a restoring roll moment toward wings-level. The vertical fin provides directional stability; the horizontal stabiliser provides pitch stability; and elevator trim sets a pitch reference, not a roll reference.
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303373 ### Q16: How does increasing altitude affect true airspeed (TAS) for a given indicated airspeed (IAS)? ^t80q16
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305375 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q16) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q16)
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324394 - **ρ** (rho) — air density
325395 - **TAS** = True Airspeed
326396 - **ρ₀** — air density at sea level (ISA: 1.225 kg/m³)
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+- Examen Blanc: [VV Q36 p.187](Questionnaire%20toutes%20branches%20VV.pdf#page=187) (score: 0.29)
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+- PDF Answer: D
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327403 ### Q17: What does the term "load factor" describe? ^t80q17
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329405 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q17) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q17)
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347423 - **L** — Lift — aerodynamic force acting perpendicular to the airflow
348424 - **g** — gravitational acceleration (9.81 m/s²)
349425 - **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
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+- Examen Blanc: [VV Q13 p.77](Questionnaire%20toutes%20branches%20VV.pdf#page=77) (score: 0.24)
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+- PDF Answer: A
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350432 ### Q18: How does increasing aircraft weight affect the best glide ratio? ^t80q18
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352434 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q18) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q18)
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364446 
365447 The best L/D ratio is determined by the aerodynamic shape of the aircraft and is independent of weight. Increasing weight shifts the speed polar downward and to the right — the best glide speed increases (must fly faster) but the maximum L/D ratio stays the same. This is why adding water ballast in gliders improves inter-thermal cruise speed without changing the glide angle — only the speed at which that angle is achieved changes.
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367453 ### Q19: A glider is flying at the speed for minimum sink rate. If the pilot accelerates, what happens to the sink rate? ^t80q19
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369455 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q19) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q19)
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380466 #### Explanation
381467 
382468 The minimum sink rate speed is the speed at the lowest point of the speed polar. Any speed change — faster or slower — from this point increases the sink rate. Accelerating beyond minimum sink speed increases parasite drag faster than induced drag decreases, resulting in a higher total drag and therefore a greater rate of descent. This is the trade-off in cross-country flying: flying faster covers more ground but at the cost of increased sink rate.
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+- Examen Blanc: [VV Q20 p.78](Questionnaire%20toutes%20branches%20VV.pdf#page=78) (score: 0.21)
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+- PDF Answer: C
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384476 ### Q20: What is the effect of extending airbrakes (spoilers) on a glider? ^t80q20
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399491 #### Explanation
400492 
401493 Airbrakes (spoilers) disrupt the smooth airflow over the wing surface, reducing the pressure differential and therefore reducing lift. Simultaneously, the raised spoiler panels create a large increase in drag. This combined effect steepens the glide path dramatically, which is precisely their purpose — to allow the pilot to control the approach angle and land precisely. Without airbrakes, gliders would float long distances due to their excellent L/D ratio.
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+- Examen Blanc: [S2 Q18 p.27](Exa%20Blanc%20Série_2.pdf#page=27) (score: 0.25)
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403500 ### Q21: In which flight condition is induced drag greatest? ^t80q21
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420517 #### Key Terms
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422519 CL — Lift Coefficient — dimensionless measure of aerodynamic lift
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+- Examen Blanc: [S1S Q13 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.22)
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+- PDF Answer: A
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423526 ### Q22: What is the primary function of an elevator trim tab? ^t80q22
424527 
425528 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q22) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q22)
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437540 
438541 The elevator trim tab allows the pilot to reduce or eliminate the stick force needed to hold a given pitch attitude in steady flight. By deflecting the trim tab, an aerodynamic force is applied to the elevator that counters the natural hinge moment, allowing hands-off or reduced-force flight at the trimmed speed. This reduces pilot fatigue on long flights and allows the pilot to concentrate on navigation and thermal exploitation.
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440547 ### Q23: What happens to stall speed in a turn compared to straight-and-level flight? ^t80q23
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442549 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q23) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q23)
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457564 #### Key Terms
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459566 n — Load Factor (ratio of lift to weight: n = L/W)
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+- Examen Blanc: [S1S Q18 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.31)
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+- PDF Answer: C
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461574 ### Q24: What is the centre of pressure of an aerofoil? ^t80q24
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480593 - **AoA** = Angle of Attack
481594 - **CG** = Centre of Gravity
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+- Examen Blanc: [VV Q15 p.214](Questionnaire%20toutes%20branches%20VV.pdf#page=214) (score: 0.24)
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+- PDF Answer: D
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482601 ### Q25: At what point during flight is parasite drag greatest? ^t80q25
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484603 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q25) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q25)
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499618 #### Key Terms
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501620 VNE — Never Exceed Speed
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+- Examen Blanc: [VV Q50 p.64](Questionnaire%20toutes%20branches%20VV.pdf#page=64) (score: 0.21)
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+- PDF Answer: B
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502627 ### Q26: What is the Bernoulli principle as applied to an aerofoil? ^t80q26
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516641 
517642 Bernoulli's principle states that in a steady, incompressible flow, an increase in flow velocity is accompanied by a decrease in static pressure, and vice versa. Applied to an aerofoil, the air accelerates over the curved upper surface, creating a region of lower pressure compared to the lower surface. This pressure differential generates lift. While Newton's third law (downwash) also contributes to lift, the Bernoulli pressure distribution is the primary mechanism for conventional subsonic flight.
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519648 ### Q27: What is adverse yaw? ^t80q27
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521650 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q27) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q27)
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533662 
534663 Adverse yaw occurs because the down-going aileron (on the wing that rises) increases both lift and induced drag on that wing. The extra drag on the rising wing pulls the nose toward the descending wing — opposite to the intended turn direction. This is why coordinated use of rudder with aileron is essential, and why differential aileron deflection was developed as a design solution.
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536669 ### Q28: When does ground effect become significant? ^t80q28
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553686 #### Key Terms
554687 
555688 AGL = Above Ground Level
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556693 ### Q29: What does the term "washout" refer to in wing design? ^t80q29
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558695 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q29) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q29)
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571708 Washout is a deliberate design feature in which the wing's angle of incidence decreases progressively from root to tip (geometric washout) or the aerofoil section changes to produce less lift at the tip (aerodynamic washout). This ensures that the wing root stalls before the tip, preserving aileron effectiveness during a stall and making the stall behaviour more benign and recoverable. Washout is particularly important in gliders with their long, high-aspect-ratio wings.
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573714 ### Q30: What is the relationship between the angle of attack and the lift coefficient up to the stall? ^t80q30
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575716 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q30) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q30)
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600741 - **CL** = Lift Coefficient
601742 - **AoA** = Angle of Attack
602743 - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
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603748 ### Q31: How does the flap position affect the stall speed? ^t80q31
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625770 - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
626771 - **VS** = Stall Speed
627772 - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
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+- Examen Blanc: [VV Q19 p.183](Questionnaire%20toutes%20branches%20VV.pdf#page=183) (score: 0.25)
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+- PDF Answer: D
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628779 ### Q32: What is the purpose of a laminar-flow aerofoil? ^t80q32
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630781 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q32) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q32)
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642793 
643794 Laminar-flow aerofoils are designed with their maximum thickness further aft than conventional profiles, creating a favourable pressure gradient that keeps the boundary layer laminar over a larger portion of the chord. Since laminar boundary layers produce far less skin friction drag than turbulent ones, the overall profile drag is significantly reduced. Gliders exploit this extensively — clean laminar-flow wings are the reason modern gliders achieve glide ratios exceeding 50:1.
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645800 ### Q33: How does air density change with increasing altitude? ^t80q33
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664819 - **TAS** = True Airspeed
665820 - **IAS** = Indicated Airspeed
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+- Examen Blanc: [VV Q30 p.113](Questionnaire%20toutes%20branches%20VV.pdf#page=113) (score: 0.28)
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+- PDF Answer: D
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666827 ### Q34: What is the difference between static stability and dynamic stability? ^t80q34
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....@@ -680,6 +841,10 @@
680841 
681842 Static stability describes the aircraft's immediate response to a disturbance — whether restoring forces act to push it back toward the original equilibrium. Dynamic stability describes what happens over time: if the resulting oscillations decrease in amplitude and the aircraft eventually returns to its trimmed state, it is dynamically stable. An aircraft can be statically stable but dynamically unstable (oscillations grow), which is a dangerous condition.
682843 
844
+
845
+#### Source
846
+
847
+- [?] Source non identifiée
683848 ### Q35: What is the purpose of vortex generators on a wing? ^t80q35
684849 
685850 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q35) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q35)
....@@ -697,6 +862,10 @@
697862 
698863 Vortex generators are small tabs that protrude from the wing surface and create tiny vortices that mix high-energy air from outside the boundary layer into the slower boundary layer flow near the surface. This energised boundary layer can resist adverse pressure gradients more effectively, delaying flow separation and improving control effectiveness at high angles of attack. They trade a small increase in skin friction for a significant delay in stall onset and better aileron authority near the stall.
699864 
865
+
866
+#### Source
867
+
868
+- [?] Source non identifiée
700869 ### Q36: Which of the following factors does a pilot directly control that affects lift? ^t80q36
701870 
702871 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q36) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q36)
....@@ -717,6 +886,12 @@
717886 #### Key Terms
718887 
719888 CL = Lift Coefficient
889
+
890
+#### Source
891
+
892
+- Examen Blanc: [VV Q95 p.231](Questionnaire%20toutes%20branches%20VV.pdf#page=231) (score: 0.22)
893
+- PDF Answer: B
894
+
720895 ### Q37: In which direction does the centre of pressure move as the angle of attack increases (pre-stall)? ^t80q37
721896 
722897 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q37) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q37)
....@@ -737,6 +912,12 @@
737912 #### Key Terms
738913 
739914 AoA = Angle of Attack
915
+
916
+#### Source
917
+
918
+- Examen Blanc: [VV Q16 p.214](Questionnaire%20toutes%20branches%20VV.pdf#page=214) (score: 0.40)
919
+- PDF Answer: C
920
+
740921 ### Q38: What determines the critical angle of attack at which a wing stalls? ^t80q38
741922 
742923 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q38) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q38)
....@@ -754,6 +935,10 @@
754935 
755936 The critical angle of attack is an inherent property of the aerofoil's geometric shape — it is the angle at which the flow can no longer remain attached to the upper surface and separates, causing the stall. It does not change with weight, altitude, or airspeed. What changes with those factors is the stall speed — the speed at which the wing reaches the critical angle of attack in level flight. The aerofoil geometry (camber, thickness, leading edge radius) determines how well the flow follows the upper surface at high angles.
756937 
938
+
939
+#### Source
940
+
941
+- [?] Source non identifiée
757942 ### Q39: How does induced drag behave with increasing airspeed in level flight? ^t80q39
758943 
759944 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q39) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q39)
....@@ -780,6 +965,12 @@
780965 - **S** — Wing Area — total planform area of the wings
781966 - **AR** — Aspect Ratio — ratio of wingspan² to wing area
782967 - **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution)
968
+
969
+#### Source
970
+
971
+- Examen Blanc: [VV Q171 p.143](Questionnaire%20toutes%20branches%20VV.pdf#page=143) (score: 0.22)
972
+- PDF Answer: C
973
+
783974 ### Q40: Which types of drag make up total drag? ^t80q40
784975 
785976 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q40) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q40)
....@@ -800,6 +991,10 @@
800991 - **Options A and C** list sub-components of parasite drag but omit induced drag or incorrectly combine them.
801992 - **Option B** omits induced drag, which is a major component especially at low speeds.
802993 
994
+
995
+#### Source
996
+
997
+- [?] Source non identifiée
803998 ### Q41: How do lift and drag change when a stall is approached? ^t80q41
804999 
8051000 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q41) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q41)
....@@ -822,6 +1017,12 @@
8221017 - **AoA** = Angle of Attack
8231018 - **CL** = Lift Coefficient
8241019 - **CD** = Drag Coefficient
1020
+
1021
+#### Source
1022
+
1023
+- Examen Blanc: [S2 Q18 p.27](Exa%20Blanc%20Série_2.pdf#page=27) (score: 0.24)
1024
+- [QuizVDS Q41](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q41): Answer A
1025
+
8251026 ### Q42: To recover from a stall, it is essential to ^t80q42
8261027 
8271028 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q42) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q42)
....@@ -842,6 +1043,10 @@
8421043 #### Key Terms
8431044 
8441045 AoA = Angle of Attack
1046
+
1047
+#### Source
1048
+
1049
+- [?] Source non identifiée
8451050 ### Q43: During a stall, how do lift and drag behave? ^t80q43
8461051 
8471052 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q43) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q43)
....@@ -873,6 +1078,13 @@
8731078 - **AoA** = Angle of Attack
8741079 - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
8751080 - **CD** = Drag Coefficient
1081
+
1082
+#### Source
1083
+
1084
+- Examen Blanc: [VV Q19 p.183](Questionnaire%20toutes%20branches%20VV.pdf#page=183) (score: 0.20)
1085
+- [QuizVDS Q41](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q41): Answer A
1086
+- PDF Answer: D
1087
+
8761088 ### Q44: The critical angle of attack ^t80q44
8771089 
8781090 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q44) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q44)
....@@ -899,6 +1111,13 @@
8991111 - **AoA** = Angle of Attack
9001112 - **VS** = Stall Speed
9011113 - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
1114
+
1115
+#### Source
1116
+
1117
+- Examen Blanc: [VV Q48 p.221](Questionnaire%20toutes%20branches%20VV.pdf#page=221) (score: 0.26)
1118
+- [QuizVDS Q44](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q44): Answer C
1119
+- PDF Answer: D
1120
+
9021121 ### Q45: What leads to a lower stall speed Vs (IAS)? ^t80q45
9031122 
9041123 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q45) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q45)
....@@ -928,6 +1147,13 @@
9281147 - **n** — Load Factor (ratio of lift to weight: n = L/W)
9291148 - **VS** = Stall Speed
9301149 - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
1150
+
1151
+#### Source
1152
+
1153
+- Examen Blanc: [VV Q19 p.183](Questionnaire%20toutes%20branches%20VV.pdf#page=183) (score: 0.21)
1154
+- [QuizVDS Q45](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q45): Answer B
1155
+- PDF Answer: D
1156
+
9311157 ### Q46: Which statement about a spin is correct? ^t80q46
9321158 
9331159 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q46) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q46)
....@@ -948,6 +1174,10 @@
9481174 #### Key Terms
9491175 
9501176 AoA = Angle of Attack
1177
+
1178
+#### Source
1179
+
1180
+- [?] Source non identifiée
9511181 ### Q47: The laminar boundary layer on the aerofoil lies between ^t80q47
9521182 
9531183 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q47) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q47)
....@@ -966,6 +1196,13 @@
9661196 #### Explanation
9671197 
9681198 The boundary layer development follows a specific sequence: flow is divided at the stagnation point, a laminar boundary layer develops from the stagnation point rearward, then at the transition point the laminar layer converts to turbulent, and finally at the separation point the turbulent layer detaches from the surface. The laminar boundary layer therefore occupies the region from the stagnation point to the transition point. Laminar flow aerofoils are designed to push the transition point as far aft as possible to minimise friction drag.
1199
+
1200
+
1201
+#### Source
1202
+
1203
+- Examen Blanc: [S1S Q17 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.25)
1204
+- [QuizVDS Q47](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q47): Answer B
1205
+- PDF Answer: C
9691206 
9701207 ### Q48: What types of boundary layers are found on an aerofoil? ^t80q48
9711208 
....@@ -986,6 +1223,10 @@
9861223 
9871224 The natural sequence of boundary layer development on an aerofoil runs from laminar (near the leading edge, where the flow is orderly and Reynolds number is low) to turbulent (further aft, after transition). The reverse sequence (turbulent first, then laminar) does not occur naturally. This forward laminar / aft turbulent arrangement is why designers place the maximum thickness of laminar-flow aerofoils further back — to extend the favourable pressure gradient that maintains laminar flow as far as possible before transition.
9881225 
1226
+
1227
+#### Source
1228
+
1229
+- [?] Source non identifiée
9891230 ### Q49: How does a laminar boundary layer differ from a turbulent one? ^t80q49
9901231 
9911232 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q49) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q49)
....@@ -1003,6 +1244,10 @@
10031244 
10041245 The turbulent boundary layer, despite having higher skin friction drag than the laminar layer, has more energetic mixing that allows it to remain attached to the surface against an adverse pressure gradient at higher angles of attack. This is its critical advantage: it resists flow separation better. The laminar boundary layer is indeed thinner (C is partly correct about thickness) and has lower friction drag — but it separates more easily. This is why turbulators are sometimes used on gliders: deliberately triggering transition to turbulent flow to prevent laminar separation bubbles.
10051246 
1247
+
1248
+#### Source
1249
+
1250
+- [?] Source non identifiée
10061251 ### Q50: Which structural element provides lateral (roll) stability? ^t80q50
10071252 
10081253 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q50) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q50)
....@@ -1022,6 +1267,10 @@
10221267 
10231268 Lateral (roll) stability — the tendency to return to wings-level after a roll disturbance — is primarily provided by wing dihedral (the upward angle of the wings from horizontal). When a gust rolls the aircraft, the lower wing descends and its angle of attack increases (it meets more airflow), generating more lift and creating a restoring moment back to level. The vertical tail provides directional (yaw) stability; ailerons are roll control surfaces (not stability), and the elevator controls pitch. High-wing aircraft achieve similar lateral stability through the pendulum effect of the fuselage hanging below the wings.
10241269 
1270
+
1271
+#### Source
1272
+
1273
+- [?] Source PDF non identifiée (original: **A**)
10251274 ### Q51: What is the mean value of gravitational acceleration at the Earth's surface? ^t80q51
10261275 
10271276 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q51) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q51)
....@@ -1043,6 +1292,12 @@
10431292 
10441293 - **ISA** = International Standard Atmosphere
10451294 - **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
1295
+
1296
+#### Source
1297
+
1298
+- Examen Blanc: [S1S Q2 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.82)
1299
+- PDF Answer: D
1300
+
10461301 ### Q52: During a sideslip, the permitted flap position is ^t80q52
10471302 
10481303 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q52) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q52)
....@@ -1059,6 +1314,12 @@
10591314 #### Explanation
10601315 
10611316 The permitted flap position during a sideslip is always specified in the aircraft flight manual (AFM/POH). Some gliders prohibit extended flaps in a sideslip because the combination of flaps and deflected rudder can create dangerous aerodynamic couples or exceed structural limits. Others permit certain configurations. The only correct answer is therefore to consult the AFM.
1317
+
1318
+
1319
+#### Source
1320
+
1321
+- Examen Blanc: [S1S Q15 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.65)
1322
+- PDF Answer: A
10621323 
10631324 ### Q53: An aircraft is said to have dynamic stability when ^t80q53
10641325 
....@@ -1077,6 +1338,12 @@
10771338 
10781339 Dynamic stability describes the behaviour of an aircraft over time after a disturbance. A dynamically stable aircraft returns automatically to its original equilibrium (trim) after being disturbed — the oscillations progressively damp out. Answer A describes so-called "neutral or convergent stability towards a new equilibrium", which is different. Static stability (the immediate tendency to return) is a necessary but not sufficient condition for dynamic stability.
10791340 
1341
+
1342
+#### Source
1343
+
1344
+- Examen Blanc: [S1S Q19 p.43](Exa%20Blanc%20Série_1_Specifiques.pdf#page=43) (score: 0.88)
1345
+- PDF Answer: A
1346
+
10801347 ### Q54: In severe turbulence, airspeed must be reduced ^t80q54
10811348 
10821349 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q54) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q54)
....@@ -1093,6 +1360,12 @@
10931360 #### Explanation
10941361 
10951362 The manoeuvring speed V_A (or turbulence penetration speed) is the maximum speed at which full control surface deflections or severe wind gusts will not cause the structural limit load to be exceeded. Below V_A, the wing will stall before the structural limit load is reached, thereby protecting the structure. In severe turbulence, speed must be reduced below V_A to avoid structural damage from gust dynamic loads.
1363
+
1364
+
1365
+#### Source
1366
+
1367
+- Examen Blanc: [VV Q19 p.78](Questionnaire%20toutes%20branches%20VV.pdf#page=78) (score: 0.22)
1368
+- PDF Answer: D
10961369 
10971370 ### Q55: In the ICAO standard atmosphere, the temperature lapse rate in the troposphere is ^t80q55
10981371 
....@@ -1115,6 +1388,12 @@
11151388 
11161389 - **ISA** = International Standard Atmosphere
11171390 - **ICAO** = International Civil Aviation Organization
1391
+
1392
+#### Source
1393
+
1394
+- Examen Blanc: [S1S Q1 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.70)
1395
+- PDF Answer: D
1396
+
11181397 ### Q56: At approximately what altitude does atmospheric pressure fall to half its sea-level value? ^t80q56
11191398 
11201399 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q56) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q56)
....@@ -1135,6 +1414,12 @@
11351414 #### Key Terms
11361415 
11371416 ICAO = International Civil Aviation Organization
1417
+
1418
+#### Source
1419
+
1420
+- Examen Blanc: [S1S Q3 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.54)
1421
+- PDF Answer: C
1422
+
11381423 ### Q57: Density altitude always corresponds to ^t80q57
11391424 
11401425 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q57) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q57)
....@@ -1156,6 +1441,12 @@
11561441 
11571442 - **ISA** = International Standard Atmosphere
11581443 - **QNH** = Pressure adjusted to mean sea level
1444
+
1445
+#### Source
1446
+
1447
+- Examen Blanc: [S1S Q4 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.66)
1448
+- PDF Answer: C
1449
+
11591450 ### Q58: The simplified continuity law applied to an airflow states: *In a given period of time, a flowing air mass is conserved regardless of the cross-section it passes through.* This means that ^t80q58
11601451 
11611452 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q58) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q58)
....@@ -1177,6 +1468,12 @@
11771468 
11781469 - **S** — Wing Area — total planform area of the wings
11791470 - **V** — Velocity / Airspeed
1471
+
1472
+
1473
+#### Source
1474
+
1475
+- Examen Blanc: [S1S Q5 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.70)
1476
+- PDF Answer: A
11801477 
11811478 ### Q59: The aerodynamic resultant (drag and lift) depends on air density. When air density decreases ^t80q59
11821479 
....@@ -1200,6 +1497,12 @@
12001497 - **q** — dynamic pressure (q = ½ × ρ × V²)
12011498 - **ρ** (rho) — air density
12021499 - **TAS** = True Airspeed
1500
+
1501
+#### Source
1502
+
1503
+- Examen Blanc: [S1S Q6 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.52)
1504
+- PDF Answer: A
1505
+
12031506 ### Q60: What is the name of the point about which, when the angle of attack changes, the pitching moment around the lateral axis does not vary? ^t80q60
12041507 
12051508 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q60) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q60)
....@@ -1220,6 +1523,12 @@
12201523 #### Key Terms
12211524 
12221525 CG — Centre of Gravity
1526
+
1527
+#### Source
1528
+
1529
+- Examen Blanc: [S1S Q11 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.65)
1530
+- PDF Answer: D
1531
+
12231532 ### Q61: The angle between the aerofoil chord line and the aircraft's longitudinal axis is called ^t80q61
12241533 
12251534 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q61) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q61)
....@@ -1236,6 +1545,16 @@
12361545 #### Explanation
12371546 
12381547 The rigging angle (or angle of incidence) is the fixed angle, defined at construction, between the aerofoil chord line and the longitudinal axis of the fuselage. It does not vary in flight. It should not be confused with the angle of attack, which is the angle between the chord line and the direction of the relative wind (and which varies in flight according to attitude and speed). The rigging angle is chosen by the manufacturer so that the wing generates the necessary lift in cruise at an aerodynamically favourable fuselage attitude.
1548
+
1549
+![](figures/t80_q90.png)
1550
+
1551
+The chord line (**A** in the diagram) is the straight reference line from leading edge to trailing edge. The rigging angle is measured between this line and the fuselage axis.
1552
+
1553
+
1554
+#### Source
1555
+
1556
+- Examen Blanc: [S1S Q9 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.56)
1557
+- PDF Answer: D
12391558 
12401559 ### Q62: What does the transition point correspond to? ^t80q62
12411560 
....@@ -1254,6 +1573,12 @@
12541573 
12551574 The transition point is precisely the location on the aerofoil where the boundary layer changes from a laminar regime (ordered flow, in parallel layers) to a turbulent regime (disordered flow, with transverse mixing). This transition is irreversible in the direction of flow: the change is from laminar to turbulent, never the reverse. The position of the transition point depends on the Reynolds number, the pressure gradient, and surface roughness — a favourable pressure gradient (acceleration) maintains laminar flow, while an adverse gradient (deceleration) triggers transition.
12561575 
1576
+
1577
+#### Source
1578
+
1579
+- Examen Blanc: [S1S Q17 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.65)
1580
+- PDF Answer: C
1581
+
12571582 ### Q63: Geometric or aerodynamic wing twist results in ^t80q63
12581583 
12591584 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q63) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q63)
....@@ -1271,6 +1596,12 @@
12711596 
12721597 Wing twist (geometric or aerodynamic) varies the angle of incidence or aerodynamic characteristics along the span, so that the stall does not occur simultaneously across the entire wing. The root (higher angle of incidence) reaches the critical angle first and stalls progressively, while the outer sections remain attached. This progressive (rather than simultaneous) flow separation improves stall safety and maintains roll control via the ailerons. The effect on adverse yaw ****(A)**** is indirect and marginal.
12731598 
1599
+
1600
+#### Source
1601
+
1602
+- Examen Blanc: [S1S Q10 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.61)
1603
+- PDF Answer: B
1604
+
12741605 ### Q64: The profile drag (form drag) of a body is primarily influenced by ^t80q64
12751606 
12761607 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q64) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q64)
....@@ -1287,6 +1618,12 @@
12871618 #### Explanation
12881619 
12891620 Form drag (pressure drag) is caused by the pressure difference between the front and rear of a body, due to boundary layer separation and the formation of vortices in the wake. The more intense the vortex formation (unStreamlined body, blunt trailing edge), the higher the form drag. This is why streamlined aerofoils have much lower form drag than a flat plate or sphere — their progressively converging shape allows the flow to remain attached longer, reducing the turbulent wake.
1621
+
1622
+
1623
+#### Source
1624
+
1625
+- Examen Blanc: [S1S Q14 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.71)
1626
+- PDF Answer: C
12901627 
12911628 ### Q65: The aerodynamic drag of a flat disc in an airflow depends notably on ^t80q65
12921629 
....@@ -1312,6 +1649,12 @@
13121649 - **ρ** (rho) — air density
13131650 - **D** — Drag
13141651 - **CD** = Drag Coefficient
1652
+
1653
+#### Source
1654
+
1655
+- Examen Blanc: [S1S Q12 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.68)
1656
+- PDF Answer: B
1657
+
13151658 ### Q66: On the speed polar, which tangent touches the curve at the point of minimum sink rate? ^t80q66
13161659 
13171660 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q66) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q66)
....@@ -1340,6 +1683,12 @@
13401683 
13411684 The other tangents: **(B)** from the origin gives best L/D (best glide angle). **(C)** from a right-shifted point on V compensates for headwind. **(A)** from a point above the origin on the W axis is the McCready tangent for optimal inter-thermal cruise speed.
13421685 
1686
+
1687
+#### Source
1688
+
1689
+- Examen Blanc: [S1S Q16 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.55)
1690
+- PDF Answer: C
1691
+
13431692 ### Q67: Induced drag increases ^t80q67
13441693 
13451694 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q67) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q67)
....@@ -1367,6 +1716,12 @@
13671716 - **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution)
13681717 - **q** — dynamic pressure (q = ½ × ρ × V²)
13691718 - **S** — Wing Area — total planform area of the wings
1719
+
1720
+#### Source
1721
+
1722
+- Examen Blanc: [S1S Q13 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.33)
1723
+- PDF Answer: A
1724
+
13701725 ### Q68: How does the minimum speed of an aircraft in a level turn at 45-degree bank compare to straight-and-level flight? ^t80q68
13711726 
13721727 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q68) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q68)
....@@ -1388,6 +1743,12 @@
13881743 
13891744 - **n** — Load Factor (ratio of lift to weight: n = L/W)
13901745 - **VS** = Stall Speed
1746
+
1747
+#### Source
1748
+
1749
+- Examen Blanc: [S1S Q18 p.42](Exa%20Blanc%20Série_1_Specifiques.pdf#page=42) (score: 0.33)
1750
+- PDF Answer: C
1751
+
13911752 ### Q69: Adverse yaw is caused by ^t80q69
13921753 
13931754 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q69) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q69)
....@@ -1404,6 +1765,12 @@
14041765 #### Explanation
14051766 
14061767 Adverse yaw is caused by the asymmetry of drag between the two ailerons during turn entry. The aileron that rises (on the high-wing side) increases the local angle of attack, generating more lift but also more induced drag. This additional drag on the rising side creates a yawing moment towards the rising side — i.e. in the opposite direction to the turn (hence "adverse yaw"). Differential ailerons and spoiler-airbrakes are technical solutions to mitigate this effect.
1768
+
1769
+
1770
+#### Source
1771
+
1772
+- Examen Blanc: [S1S Q8 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.59)
1773
+- PDF Answer: D
14071774 
14081775 ### Q70: True Airspeed (TAS) is the speed shown by the ASI ^t80q70
14091776 
....@@ -1427,6 +1794,12 @@
14271794 - **TAS** = True Airspeed
14281795 - **IAS** = Indicated Airspeed
14291796 - **CAS** = Calibrated Airspeed
1797
+
1798
+#### Source
1799
+
1800
+- Examen Blanc: [S1S Q7 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.65)
1801
+- PDF Answer: D
1802
+
14301803 ### Q71: The speed range authorised for the use of slotted flaps is: ^t80q71
14311804 
14321805 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q71) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q71)
....@@ -1447,6 +1820,11 @@
14471820 #### Key Terms
14481821 
14491822 VA = Manoeuvring Speed
1823
+
1824
+#### Source
1825
+
1826
+- Examen Blanc: [S2 Q1 p.37](Exa%20Blanc%20Série_2.pdf#page=37) (score: 0.43)
1827
+
14501828 ### Q72: Wing tip vortices are caused by pressure equalisation from: ^t80q72
14511829 
14521830 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q72) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q72)
....@@ -1464,6 +1842,11 @@
14641842 
14651843 Wing tip vortices (induced vortices) come from pressure equalization from the lower surface (high pressure) to the upper surface (low pressure) at the wing tip. This phenomenon generates induced drag.
14661844 
1845
+
1846
+#### Source
1847
+
1848
+- Examen Blanc: [S2 Q2 p.37](Exa%20Blanc%20Série_2.pdf#page=37) (score: 0.33)
1849
+
14671850 ### Q73: The angle of attack of an aerofoil is always the angle between: ^t80q73
14681851 
14691852 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q73) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q73)
....@@ -1480,6 +1863,16 @@
14801863 #### Explanation
14811864 
14821865 Angle of attack is the angle between the chord line and the general airflow direction (relative wind direction). It is not the angle with the horizon nor with the longitudinal axis.
1866
+
1867
+![](figures/t80_q90.png)
1868
+
1869
+The chord line (**A** in the diagram) is the straight line from leading edge (**C**) to trailing edge. The angle of attack is measured between this line and the relative airflow.
1870
+
1871
+
1872
+#### Source
1873
+
1874
+- Examen Blanc: [S2 Q3 p.37](Exa%20Blanc%20Série_2.pdf#page=37) (score: 0.65)
1875
+- [QuizVDS Q14](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q14): Answer B
14831876 
14841877 ### Q74: In the standard atmosphere, the values of temperature and atmospheric pressure at sea level are: ^t80q74
14851878 
....@@ -1511,6 +1904,11 @@
15111904 - **ICAO** = International Civil Aviation Organization
15121905 - **hPa** = hectopascal (= mbar)
15131906 - **inHg** = inches of mercury
1907
+
1908
+#### Source
1909
+
1910
+- Examen Blanc: [S2 Q4 p.37](Exa%20Blanc%20Série_2.pdf#page=37) (score: 0.91)
1911
+
15141912 ### Q75: Regarding airflow, the simplified continuity equation states: At the same moment, the same mass of air passes through different cross-sections. Therefore: ^t80q75
15151913 
15161914 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q75) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q75)
....@@ -1530,6 +1928,11 @@
15301928 
15311929 The mean camber line is the line equidistant between the lower and upper surfaces. In the figure, it is represented by line B.
15321930 
1931
+
1932
+#### Source
1933
+
1934
+- Examen Blanc: [S3 Q20 p.41](Exa%20Blanc%20Série_3.pdf#page=41) (score: 0.42)
1935
+
15331936 ### Q76: In a correctly executed turn without altitude loss, why is slight back-pressure on the elevator necessary? ^t80q76
15341937 
15351938 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q76) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q76)
....@@ -1546,6 +1949,11 @@
15461949 #### Explanation
15471950 
15481951 In a coordinated turn without altitude loss, back pressure is needed to increase lift and balance centrifugal force (load factor > 1). Lift must compensate for both gravity and centrifugal force.
1952
+
1953
+
1954
+#### Source
1955
+
1956
+- Examen Blanc: [S3 Q6 p.38](Exa%20Blanc%20Série_3.pdf#page=38) (score: 0.53)
15491957 
15501958 ### Q77: When the frontal area of a disc in an airflow is tripled, drag increases by: ^t80q77
15511959 
....@@ -1578,6 +1986,11 @@
15781986 - **V** — Velocity / Airspeed
15791987 - **Cd** — Drag Coefficient — dimensionless shape-dependent factor
15801988 - **A** — Frontal Area — cross-sectional area perpendicular to the airflow
1989
+
1990
+
1991
+#### Source
1992
+
1993
+- Examen Blanc: [S2 Q7 p.38](Exa%20Blanc%20Série_2.pdf#page=38) (score: 0.64)
15811994 
15821995 ### Q78: Aerodynamic wing twist (washout) is a modification of: ^t80q78
15831996 
....@@ -1615,6 +2028,11 @@
16152028 - **Dihedral** — upward angle of the wing from root to tip for lateral stability
16162029 
16172030 
2031
+
2032
+#### Source
2033
+
2034
+- Examen Blanc: [S2 Q8 p.38](Exa%20Blanc%20Série_2.pdf#page=38) (score: 0.75)
2035
+
16182036 ### Q79: What is the average value of gravitational acceleration at the Earth's surface? ^t80q79
16192037 
16202038 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q79) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q79)
....@@ -1635,6 +2053,12 @@
16352053 #### Key Terms
16362054 
16372055 ISA = International Standard Atmosphere
2056
+
2057
+#### Source
2058
+
2059
+- Examen Blanc: [S1S Q2 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.82)
2060
+- PDF Answer: D
2061
+
16382062 ### Q80: The speed displayed on the airspeed indicator (ASI) is a measurement of: ^t80q80
16392063 
16402064 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q80) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q80)
....@@ -1651,6 +2075,11 @@
16512075 #### Explanation
16522076 
16532077 Airspeed indicator reading is based on the difference between static pressure and total pressure (dynamic pressure). The ASI measures this difference via the Pitot tube and static port.
2078
+
2079
+
2080
+#### Source
2081
+
2082
+- Examen Blanc: [S2 Q10 p.38](Exa%20Blanc%20Série_2.pdf#page=38) (score: 0.72)
16542083 
16552084 ### Q81: The horizontal and vertical stabilisers serve in particular to: ^t80q81
16562085 
....@@ -1670,6 +2099,11 @@
16702099 #### Explanation
16712100 
16722101 The horizontal and vertical stabilizers serve primarily to stabilize the aircraft in flight (longitudinal and directional stability). Without them, the aircraft would be unstable.
2102
+
2103
+
2104
+#### Source
2105
+
2106
+- Examen Blanc: [S2 Q11 p.38](Exa%20Blanc%20Série_2.pdf#page=38) (score: 0.36)
16732107 
16742108 ### Q82: When slotted flaps are extended, airflow separation: ^t80q82
16752109 
....@@ -1691,6 +2125,10 @@
16912125 #### Key Terms
16922126 
16932127 CL = Lift Coefficient
2128
+
2129
+#### Source
2130
+
2131
+- [?] Source non identifiée
16942132 ### Q83: The aerodynamic centre of an aerofoil in an airflow is the point of application of: ^t80q83
16952133 
16962134 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q83) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q83)
....@@ -1712,6 +2150,11 @@
17122150 - **C (tyre pressure)** is irrelevant to aerodynamics.
17132151 - **D (airflow at the leading edge)** describes the stagnation point, not the aerodynamic centre.
17142152 
2153
+
2154
+#### Source
2155
+
2156
+- Examen Blanc: [S2 Q13 p.39](Exa%20Blanc%20Série_2.pdf#page=39) (score: 0.89)
2157
+
17152158 ### Q84: Pressures are expressed in: ^t80q84
17162159 
17172160 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q84) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q84)
....@@ -1728,6 +2171,11 @@
17282171 #### Explanation
17292172 
17302173 Pressures are expressed in bar, psi (pounds per square inch) and Pa (Pascal). g is an acceleration, not a pressure. Alpha (a) is not a pressure unit.
2174
+
2175
+
2176
+#### Source
2177
+
2178
+- Examen Blanc: [S2 Q14 p.39](Exa%20Blanc%20Série_2.pdf#page=39) (score: 0.71)
17312179 
17322180 ### Q85: TAS (True Air Speed) is the speed of: ^t80q85
17332181 
....@@ -1749,6 +2197,11 @@
17492197 #### Key Terms
17502198 
17512199 TAS = True Airspeed
2200
+
2201
+#### Source
2202
+
2203
+- Examen Blanc: [S2 Q15 p.39](Exa%20Blanc%20Série_2.pdf#page=39) (score: 0.48)
2204
+
17522205 ### Q86: Yaw stability of an aircraft is provided by: ^t80q86
17532206 
17542207 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q86) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q86)
....@@ -1765,6 +2218,11 @@
17652218 #### Explanation
17662219 
17672220 Yaw stability is provided by the fin (vertical stabilizer/rudder). Wing sweep contributes to roll stability, not yaw.
2221
+
2222
+
2223
+#### Source
2224
+
2225
+- Examen Blanc: [S2 Q16 p.39](Exa%20Blanc%20Série_2.pdf#page=39) (score: 0.30)
17682226 
17692227 ### Q87: The trailing edge flap shown below is a: ^t80q87
17702228 
....@@ -1785,6 +2243,11 @@
17852243 
17862244 The flap shown, extending from the wing with a slot, is a Slotted Flap. The slot channels air from the lower to upper surface, delaying separation.
17872245 
2246
+
2247
+#### Source
2248
+
2249
+- Examen Blanc: [S2 Q16 p.39](Exa%20Blanc%20Série_2.pdf#page=39) (score: 0.39)
2250
+
17882251 ### Q88: The risk of airflow separation on the wing occurs mainly: ^t80q88
17892252 
17902253 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q88) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q88)
....@@ -1801,6 +2264,11 @@
18012264 #### Explanation
18022265 
18032266 The risk of stall/separation appears mainly during an abrupt pull-out after a dive, as the angle of attack increases very rapidly and can exceed the critical angle before the pilot can react.
2267
+
2268
+
2269
+#### Source
2270
+
2271
+- Examen Blanc: [S2 Q18 p.40](Exa%20Blanc%20Série_2.pdf#page=40) (score: 0.53)
18042272 
18052273 ### Q89: The drag of a body in an airflow depends notably on: ^t80q89
18062274 
....@@ -1824,6 +2292,12 @@
18242292 - **ρ** (rho) — air density
18252293 ρ (rho) — air density
18262294 
2295
+
2296
+#### Source
2297
+
2298
+- Examen Blanc: [VV Q5 p.212](Questionnaire%20toutes%20branches%20VV.pdf#page=212) (score: 0.40)
2299
+- PDF Answer: D
2300
+
18272301 ### Q90: In the drawing below, the aerofoil chord is represented by: ^t80q90
18282302 
18292303 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q90) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q90)
....@@ -1837,11 +2311,33 @@
18372311 
18382312 #### Answer
18392313 
1840
-C)
2314
+D)
18412315 
18422316 #### Explanation
18432317 
1844
-The chord line is the straight line connecting the leading edge to the trailing edge. In the figure, it is represented by H.
2318
+The chord line is the straight line (dash-dot) connecting the leading edge to the trailing edge. In the figure, it is labelled **A**.
2319
+
2320
+The figure shows two lines running through the profile — don't confuse them:
2321
+- **A** (dash-dot, straight) = **chord line** — always a perfectly straight line from leading to trailing edge.
2322
+- **H** (dashed, slightly curved) = **mean camber line** — follows the midpoint between upper and lower surface. On a cambered aerofoil it curves above the chord.
2323
+
2324
+All labels in the figure:
2325
+- **A** = chord line
2326
+- **B** = leading edge radius
2327
+- **C** = leading edge point
2328
+- **D** = position of maximum thickness (distance from LE)
2329
+- **E** = maximum thickness
2330
+- **G** = extrados (upper surface)
2331
+- **H** = mean camber line
2332
+- **J** = intrados (lower surface)
2333
+- **K** = maximum camber (max distance between camber line and chord)
2334
+- **L** = chord length (total distance LE to TE)
2335
+- **M** = position of maximum camber (distance from LE)
2336
+
2337
+
2338
+#### Source
2339
+
2340
+- Examen Blanc: [S2 Q12 p.26](Exa%20Blanc%20Série_2.pdf#page=26) (score: 0.20)
18452341 
18462342 ### Q91: The angle of attack of an aerofoil is always measured between: ^t80q91
18472343 
....@@ -1860,6 +2356,10 @@
18602356 
18612357 The angle of attack (AoA) is defined as the angle between the chord line and the direction of the undisturbed relative airflow, making A correct.
18622358 
2359
+![](figures/t80_q90.png)
2360
+
2361
+The chord line (**A** in the diagram) is the straight line from leading edge (**C**) to trailing edge. The angle of attack is measured between this line and the relative airflow direction.
2362
+
18632363 - **Option B** is wrong because the longitudinal axis is a structural reference, not an aerodynamic one; AoA is measured from the chord line.
18642364 - **Option C** confuses AoA with pitch attitude, which relates the longitudinal axis to the horizon.
18652365 - **Option D** is nonsensical — AoA is a geometric and aerodynamic property entirely independent of the pilot's weight.
....@@ -1867,6 +2367,12 @@
18672367 #### Key Terms
18682368 
18692369 AoA = Angle of Attack
2370
+
2371
+#### Source
2372
+
2373
+- Examen Blanc: [S3 Q1 p.37](Exa%20Blanc%20Série_3.pdf#page=37) (score: 0.71)
2374
+- [QuizVDS Q14](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q14): Answer B
2375
+
18702376 ### Q92: Given equal frontal area and equal airflow speed, what determines the drag of a body? ^t80q92
18712377 
18722378 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q92) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q92)
....@@ -1893,6 +2399,11 @@
18932399 - **CD** = Drag Coefficient
18942400 - **rho** — ρ (rho) — air density
18952401 - **S** — Wing Area — total planform area of the wings
2402
+
2403
+#### Source
2404
+
2405
+- Examen Blanc: [S3 Q2 p.37](Exa%20Blanc%20Série_3.pdf#page=37) (score: 0.50)
2406
+
18962407 ### Q93: What is the origin of induced drag on a wing? ^t80q93
18972408 
18982409 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q93) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q93)
....@@ -1913,6 +2424,11 @@
19132424 - **Option D** reverses the flow direction — air moves from high to low pressure, not the other way.
19142425 
19152426 - **Option A** describes interference drag at the wing root, and option B is too vague — airspeed alone is not the origin of induced drag.
2427
+
2428
+
2429
+#### Source
2430
+
2431
+- Examen Blanc: [S3 Q3 p.37](Exa%20Blanc%20Série_3.pdf#page=37) (score: 0.45)
19162432 
19172433 ### Q94: What is the sea-level pressure in the ICAO standard atmosphere? ^t80q94
19182434 
....@@ -1939,6 +2455,11 @@
19392455 
19402456 - **ISA** = International Standard Atmosphere
19412457 - **ICAO** = International Civil Aviation Organization
2458
+
2459
+#### Source
2460
+
2461
+- Examen Blanc: [S3 Q4 p.37](Exa%20Blanc%20Série_3.pdf#page=37) (score: 0.58)
2462
+
19422463 ### Q95: In the aerofoil diagram below, which line represents the mean camber line? ^t80q95
19432464 
19442465 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q95) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q95)
....@@ -1960,6 +2481,10 @@
19602481 
19612482 - **Options A, C, and D** represent other aerofoil features such as the chord line, thickness distribution, or surface contours, not the mean camber line.
19622483 
2484
+
2485
+#### Source
2486
+
2487
+- [?] Source non identifiée
19632488 ### Q96: In a level turn without sideslip or altitude loss, why is back pressure on the elevator necessary? ^t80q96
19642489 
19652490 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q96) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q96)
....@@ -1980,6 +2505,11 @@
19802505 - **Option A** is wrong because slips are corrected with rudder, not elevator.
19812506 - **Option B** is incorrect — the purpose is not to slow down.
19822507 - **Option C** is also wrong because skid prevention is a rudder function, not an elevator function.
2508
+
2509
+
2510
+#### Source
2511
+
2512
+- Examen Blanc: [S3 Q6 p.38](Exa%20Blanc%20Série_3.pdf#page=38) (score: 0.45)
19832513 
19842514 ### Q97: A wing stall occurs: ^t80q97
19852515 
....@@ -2006,6 +2536,11 @@
20062536 
20072537 - **VNE** = Never Exceed Speed
20082538 - **AoA** = Angle of Attack
2539
+
2540
+#### Source
2541
+
2542
+- Examen Blanc: [S3 Q7 p.38](Exa%20Blanc%20Série_3.pdf#page=38) (score: 0.43)
2543
+
20092544 ### Q98: At what condition does airflow separation from an aerofoil occur? ^t80q98
20102545 
20112546 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q98) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q98)
....@@ -2030,6 +2565,11 @@
20302565 #### Key Terms
20312566 
20322567 AoA = Angle of Attack
2568
+
2569
+#### Source
2570
+
2571
+- Examen Blanc: [S3 Q8 p.38](Exa%20Blanc%20Série_3.pdf#page=38) (score: 0.30)
2572
+
20332573 ### Q99: What is the mean gravitational acceleration at the surface of the Earth? ^t80q99
20342574 
20352575 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q99) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q99)
....@@ -2054,6 +2594,12 @@
20542594 #### Key Terms
20552595 
20562596 ISA = International Standard Atmosphere
2597
+
2598
+#### Source
2599
+
2600
+- Examen Blanc: [S1S Q2 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.73)
2601
+- PDF Answer: D
2602
+
20572603 ### Q100: True Airspeed (TAS) is obtained from the airspeed indicator (ASI) reading by: ^t80q100
20582604 
20592605 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q100) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q100)
....@@ -2081,6 +2627,11 @@
20812627 - **IAS** = Indicated Airspeed
20822628 - **CAS** = Calibrated Airspeed
20832629 - **ISA** = International Standard Atmosphere
2630
+
2631
+#### Source
2632
+
2633
+- Examen Blanc: [S3 Q10 p.39](Exa%20Blanc%20Série_3.pdf#page=39) (score: 0.39)
2634
+
20842635 ### Q101: A shift of the centre of gravity is caused by: ^t80q101
20852636 
20862637 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q101) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q101)
....@@ -2105,6 +2656,12 @@
21052656 #### Key Terms
21062657 
21072658 CG = Centre of Gravity
2659
+
2660
+#### Source
2661
+
2662
+- Examen Blanc: [VV Q16 p.77](Questionnaire%20toutes%20branches%20VV.pdf#page=77) (score: 0.50)
2663
+- PDF Answer: C
2664
+
21082665 ### Q102: The high-lift device shown in the diagram is a: ^t80q102
21092666 
21102667 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q102) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q102)
....@@ -2127,6 +2684,11 @@
21272684 - A split flap **(B)** deflects only the lower surface panel.
21282685 - A slotted flap **(C)** opens a gap but does not significantly increase wing area like the Fowler design.
21292686 
2687
+
2688
+#### Source
2689
+
2690
+- Examen Blanc: [S3 Q12 p.39](Exa%20Blanc%20Série_3.pdf#page=39) (score: 0.30)
2691
+
21302692 ### Q103: The resultant of all aerodynamic forces on a wing profile acts through the: ^t80q103
21312693 
21322694 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q103) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q103)
....@@ -2147,6 +2709,12 @@
21472709 - **Option A** is wrong because the centre of gravity is where weight acts, not aerodynamic forces.
21482710 - **Option B** is incorrect because the stagnation point is where airflow velocity is zero at the leading edge.
21492711 - **Option D** is not a standard aerodynamic term.
2712
+
2713
+
2714
+#### Source
2715
+
2716
+- Examen Blanc: [VV Q15 p.214](Questionnaire%20toutes%20branches%20VV.pdf#page=214) (score: 0.37)
2717
+- PDF Answer: D
21502718 
21512719 ### Q104: At approximately what altitude is the air density half of its sea-level value? ^t80q104
21522720 
....@@ -2172,6 +2740,11 @@
21722740 #### Key Terms
21732741 
21742742 ICAO = International Civil Aviation Organization
2743
+
2744
+#### Source
2745
+
2746
+- Examen Blanc: [S3 Q14 p.40](Exa%20Blanc%20Série_3.pdf#page=40) (score: 0.75)
2747
+
21752748 ### Q105: The airspeed indicator (ASI) reading is based on a measurement of: ^t80q105
21762749 
21772750 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q105) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q105)
....@@ -2198,6 +2771,11 @@
21982771 - **q** — dynamic pressure (q = ½ × ρ × V²)
21992772 - **rho** — ρ (rho) — air density
22002773 - **D** — Drag
2774
+
2775
+#### Source
2776
+
2777
+- Examen Blanc: [S2 Q10 p.38](Exa%20Blanc%20Série_2.pdf#page=38) (score: 0.63)
2778
+
22012779 ### Q106: Roll stability is influenced by: ^t80q106
22022780 
22032781 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q106) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q106)
....@@ -2218,6 +2796,11 @@
22182796 - **Option A** is wrong because leading-edge slats are high-lift devices that delay stall, not stability features.
22192797 - **Option B** describes pitch motion, not roll stability.
22202798 - **Option C** is incorrect because the horizontal stabiliser provides pitch (longitudinal) stability, not roll stability.
2799
+
2800
+
2801
+#### Source
2802
+
2803
+- Examen Blanc: [S3 Q16 p.40](Exa%20Blanc%20Série_3.pdf#page=40) (score: 0.64)
22212804 
22222805 ### Q107: The speed range for operating slotted flaps: ^t80q107
22232806 
....@@ -2244,6 +2827,11 @@
22442827 
22452828 - **VA** = Manoeuvring Speed
22462829 - **VNE** = Never Exceed Speed
2830
+
2831
+#### Source
2832
+
2833
+- Examen Blanc: [S3 Q17 p.40](Exa%20Blanc%20Série_3.pdf#page=40) (score: 0.62)
2834
+
22472835 ### Q108: When the wing's angle of incidence is larger at the root than at the tip, this is called: ^t80q108
22482836 
22492837 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q108) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q108)
....@@ -2268,6 +2856,11 @@
22682856 #### Key Terms
22692857 
22702858 D — Drag
2859
+
2860
+#### Source
2861
+
2862
+- Examen Blanc: [S3 Q18 p.40](Exa%20Blanc%20Série_3.pdf#page=40) (score: 0.29)
2863
+
22712864 ### Q109: Barometric pressure in the Earth's atmosphere has the characteristic of: ^t80q109
22722865 
22732866 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q109) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q109)
....@@ -2289,6 +2882,11 @@
22892882 - **Option B** is obviously false — pressure clearly drops with altitude.
22902883 - **Option C** is incorrect because pressure continues to decrease in the stratosphere; it is temperature, not pressure, that stabilises or increases in the stratosphere.
22912884 
2885
+
2886
+#### Source
2887
+
2888
+- Examen Blanc: [S3 Q18 p.40](Exa%20Blanc%20Série_3.pdf#page=40) (score: 0.31)
2889
+
22922890 ### Q110: The simplified continuity equation says the same mass of air passes through different cross-sections at the same instant. Therefore: ^t80q110
22932891 
22942892 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q110) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q110)
....@@ -2309,6 +2907,11 @@
23092907 - **Option A** is wrong because velocity does change with cross-section.
23102908 - **Option C** reverses the relationship — velocity decreases, not increases, with a larger cross-section.
23112909 - **Option D** also reverses it — velocity increases through a smaller section, not decreases.
2910
+
2911
+
2912
+#### Source
2913
+
2914
+- Examen Blanc: [S3 Q20 p.41](Exa%20Blanc%20Série_3.pdf#page=41) (score: 0.39)
23122915 
23132916 ### Q111: On the aerofoil diagram, what does point number 4 represent? ^t80q111
23142917 
....@@ -2333,6 +2936,10 @@
23332936 - **Option C** is incorrect because the centre of pressure is a theoretical force application point, not a boundary layer feature.
23342937 - **Option D** is wrong because the transition point (laminar to turbulent) occurs further forward on the surface.
23352938 
2939
+
2940
+#### Source
2941
+
2942
+- [?] Source non identifiée
23362943 ### Q112: On the aerofoil diagram, what does point number 1 represent? ^t80q112
23372944 
23382945 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q112) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q112)
....@@ -2355,6 +2962,10 @@
23552962 - **Option A** is wrong because the transition point occurs further aft where laminar flow becomes turbulent.
23562963 - **Option B** is incorrect because the centre of pressure is a resultant force point, not a physical flow location on the leading edge.
23572964 
2965
+
2966
+#### Source
2967
+
2968
+- [ ] ~ [[Examen Blanc/Exa Blanc Série_3.pdf#page=38|Série 3 Q20 p.38]]
23582969 ### Q113: What constructive feature is depicted in the figure? ^t80q113
23592970 
23602971 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q113) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q113)
....@@ -2378,6 +2989,10 @@
23782989 - **Option B** incorrectly identifies the axis — dihedral affects roll (lateral), not pitch (longitudinal) stability.
23792990 - **Option D** describes an aileron design feature unrelated to the figure.
23802991 
2992
+
2993
+#### Source
2994
+
2995
+- [?] Source non identifiée
23812996 ### Q114: "Longitudinal stability" refers to stability around which axis? ^t80q114
23822997 
23832998 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q114) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q114)
....@@ -2398,6 +3013,13 @@
23983013 - **Option A** is wrong because the vertical axis governs yaw (directional stability).
23993014 - **Option B** is incorrect because the longitudinal axis governs roll (lateral stability).
24003015 - **Option D** is not a recognised stability axis in standard aeronautical terminology.
3016
+
3017
+
3018
+#### Source
3019
+
3020
+- Examen Blanc: [S1S Q5 p.4](Exa%20Blanc%20Série_1_Specifiques.pdf#page=4) (score: 0.25)
3021
+- [QuizVDS Q53](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q53): Answer A
3022
+- PDF Answer: A
24013023 
24023024 ### Q115: Rotation about the vertical axis is termed ^t80q115
24033025 
....@@ -2420,6 +3042,13 @@
24203042 - **Option C** (rolling) is rotation around the longitudinal axis.
24213043 - **Option D** (slipping) describes a flight condition with a sideways airflow component, not a specific rotational axis.
24223044 
3045
+
3046
+#### Source
3047
+
3048
+- Examen Blanc: [S1S Q5 p.4](Exa%20Blanc%20Série_1_Specifiques.pdf#page=4) (score: 0.27)
3049
+- [QuizVDS Q56](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q56): Answer C
3050
+- PDF Answer: A
3051
+
24233052 ### Q116: Rotation about the lateral axis is termed ^t80q116
24243053 
24253054 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q116) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q116)
....@@ -2440,6 +3069,13 @@
24403069 - **Option A** (stalling) is an aerodynamic phenomenon of flow separation, not a rotational term.
24413070 - **Option B** (rolling) is rotation around the longitudinal axis.
24423071 - **Option C** (yawing) is rotation around the vertical axis.
3072
+
3073
+
3074
+#### Source
3075
+
3076
+- Examen Blanc: [VV Q75 p.69](Questionnaire%20toutes%20branches%20VV.pdf#page=69) (score: 0.27)
3077
+- [QuizVDS Q57](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q57): Answer B
3078
+- PDF Answer: B
24433079 
24443080 ### Q117: The elevator causes the aircraft to rotate around the ^t80q117
24453081 
....@@ -2463,6 +3099,12 @@
24633099 - **Option A** is wrong because the longitudinal axis governs roll, controlled by ailerons.
24643100 - **Option C** is not a standard aeronautical axis.
24653101 - **Option D** is wrong because the vertical axis governs yaw, controlled by the rudder.
3102
+
3103
+
3104
+#### Source
3105
+
3106
+- Examen Blanc: [VV Q40 p.219](Questionnaire%20toutes%20branches%20VV.pdf#page=219) (score: 0.28)
3107
+- PDF Answer: C
24663108 
24673109 ### Q118: What must be considered regarding the centre of gravity position? ^t80q118
24683110 
....@@ -2488,6 +3130,10 @@
24883130 #### Key Terms
24893131 
24903132 CG = Centre of Gravity
3133
+
3134
+#### Source
3135
+
3136
+- [?] Source non identifiée
24913137 ### Q119: What benefit does differential aileron deflection provide? ^t80q119
24923138 
24933139 ![](figures/Anatomy_sailplane_EN.png)
....@@ -2511,6 +3157,10 @@
25113157 - **Option B** is incorrect because total lift does change somewhat during aileron deflection.
25123158 - **Option C** states the opposite of the actual effect — differential ailerons decrease adverse yaw, not increase it.
25133159 
3160
+
3161
+#### Source
3162
+
3163
+- [?] Source non identifiée
25143164 ### Q120: What does the aerodynamic rudder balance accomplish? ^t80q120
25153165 
25163166 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q120) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q120)
....@@ -2532,6 +3182,10 @@
25323182 - **Option C** is wrong because stall delay is achieved by devices like slats or vortex generators, not control surface balancing.
25333183 - **Option D** makes no sense — aerodynamic balance does not reduce the size of control surfaces.
25343184 
3185
+
3186
+#### Source
3187
+
3188
+- [?] Source non identifiée
25353189 ### Q121: What purpose does static rudder (mass) balancing serve? ^t80q121
25363190 
25373191 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q121) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q121)
....@@ -2553,6 +3207,10 @@
25533207 - **Option B** is the opposite of any balancing goal.
25543208 - **Option D** is incorrect because force-free trimming is achieved by trim tabs, not mass balance.
25553209 
3210
+
3211
+#### Source
3212
+
3213
+- [?] Source non identifiée
25563214 ### Q122: When the elevator trim tab is deflected upwards, what does the trim indicator show? ^t80q122
25573215 
25583216 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q122) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q122)
....@@ -2574,6 +3232,10 @@
25743232 - **Option B** would require the tab to be neutral.
25753233 - **Option D** is the opposite — a nose-up indication would require the trim tab to deflect downward.
25763234 
3235
+
3236
+#### Source
3237
+
3238
+- [?] Source non identifiée
25773239 ### Q123: On the polar diagram, what flight condition does point number 1 indicate? ^t80q123
25783240 
25793241 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q123) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q123)
....@@ -2599,6 +3261,10 @@
25993261 
26003262 - **CL** = Lift Coefficient
26013263 - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
3264
+
3265
+#### Source
3266
+
3267
+- [?] Source non identifiée
26023268 ### Q124: In a coordinated turn, what is the relationship between load factor (n) and stall speed (Vs)? ^t80q124
26033269 
26043270 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q124) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q124)
....@@ -2624,6 +3290,13 @@
26243290 - **n** — Load Factor (ratio of lift to weight: n = L/W)
26253291 - **D** — Drag
26263292 - **VS** = Stall Speed
3293
+
3294
+#### Source
3295
+
3296
+- Examen Blanc: [VV Q26 p.185](Questionnaire%20toutes%20branches%20VV.pdf#page=185) (score: 0.20)
3297
+- [QuizVDS Q77](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q77): Answer C
3298
+- PDF Answer: B
3299
+
26273300 ### Q125: The pressure equalisation between the upper and lower wing surfaces results in ^t80q125
26283301 
26293302 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q125) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q125)
....@@ -2645,6 +3318,10 @@
26453318 - **Option B** is incorrect because vortices create turbulent, not laminar, flow.
26463319 - **Option C** is false because vortices actually reduce effective lift by reducing the local angle of attack.
26473320 
3321
+
3322
+#### Source
3323
+
3324
+- [?] Source non identifiée
26483325 ### Q126: In steady glide at equal mass, how does using a thicker aerofoil compare to a thinner one? ^t80q126
26493326 
26503327 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q126) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q126)
....@@ -2665,6 +3342,10 @@
26653342 - **Options A and C** are wrong because a thicker profile produces more, not less, drag.
26663343 - **Option B** is incorrect because lift does not decrease — it is fixed by the weight requirement in steady flight.
26673344 
3345
+
3346
+#### Source
3347
+
3348
+- [ ] ~ [[Examen Blanc/Questionnaire toutes branches VV.pdf#page=7|VV Q26 p.7]] (clé: **B**)
26683349 ### Q127: What does a profile polar diagram display? ^t80q127
26693350 
26703351 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q127) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q127)
....@@ -2690,6 +3371,10 @@
26903371 
26913372 - **CL** = Lift Coefficient
26923373 - **CD** = Drag Coefficient
3374
+
3375
+#### Source
3376
+
3377
+- [?] Source non identifiée
26933378 ### Q128: Any arbitrarily shaped body placed in an airflow (v > 0) always produces ^t80q128
26943379 
26953380 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q128) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q128)
....@@ -2710,6 +3395,12 @@
27103395 - **Option A** is wrong because drag varies with the square of velocity, not constant.
27113396 - **Option B** is physically impossible — drag-free lift does not exist.
27123397 - **Option D** is incorrect because an arbitrarily shaped body is not guaranteed to produce lift; only specifically shaped or oriented bodies generate lift.
3398
+
3399
+
3400
+#### Source
3401
+
3402
+- Examen Blanc: [S2 Q7 p.38](Exa%20Blanc%20Série_2.pdf#page=38) (score: 0.23)
3403
+- [QuizVDS Q9](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q9): Answer B
27133404 
27143405 ### Q129: In the diagram, what does number 3 represent? ^t80q129
27153406 
....@@ -2733,6 +3424,10 @@
27333424 - **Options A and B** both refer to the straight reference line from leading to trailing edge, which is a different feature.
27343425 - **Option D** (thickness) is the perpendicular distance between the upper and lower surfaces, not a line on the diagram.
27353426 
3427
+
3428
+#### Source
3429
+
3430
+- [ ] ~ [[Examen Blanc/Exa Blanc Série_3.pdf#page=37|Série 3 Q2 p.37]]
27363431 ### Q130: Which design feature can compensate for adverse yaw? ^t80q130
27373432 
27383433 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q130) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q130)
....@@ -2754,6 +3449,10 @@
27543449 - **Option B** would actually worsen adverse yaw because full deflection maximises the drag asymmetry.
27553450 - **Option D** is wrong because wing sweep primarily affects high-speed stability and critical Mach number, not adverse yaw compensation.
27563451 
3452
+
3453
+#### Source
3454
+
3455
+- [?] Source non identifiée
27573456 ### Q131: What does "wing loading" describe? ^t80q131
27583457 
27593458 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q131) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q131)
....@@ -2776,6 +3475,10 @@
27763475 - **Option B** is the inverse of wing loading.
27773476 - **Option C** (drag per wing area) is not a standard aeronautical parameter.
27783477 
3478
+
3479
+#### Source
3480
+
3481
+- [?] Source non identifiée
27793482 ### Q132: On the polar diagram, what flight state does point number 5 represent? ^t80q132
27803483 
27813484 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q132) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q132)
....@@ -2803,6 +3506,10 @@
28033506 
28043507 - **CL** = Lift Coefficient
28053508 - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
3509
+
3510
+#### Source
3511
+
3512
+- [?] Source non identifiée
28063513 ### Q133: What is the aerodynamic effect of deploying airbrakes? ^t80q133
28073514 
28083515 ![](figures/Anatomy_sailplane_EN.png)
....@@ -2825,6 +3532,12 @@
28253532 - **Option A** is wrong because lift decreases with airbrakes deployed.
28263533 - **Option B** is incorrect because drag increases, not decreases.
28273534 - **Option D** reverses both effects — airbrakes increase drag and decrease lift.
3535
+
3536
+
3537
+#### Source
3538
+
3539
+- Examen Blanc: [S1S Q6 p.40](Exa%20Blanc%20Série_1_Specifiques.pdf#page=40) (score: 0.29)
3540
+- PDF Answer: A
28283541 
28293542 ### Q134: Which combination of measures can improve the glide ratio of a sailplane? ^t80q134
28303543 
....@@ -2850,6 +3563,10 @@
28503563 #### Key Terms
28513564 
28523565 CG = Centre of Gravity
3566
+
3567
+#### Source
3568
+
3569
+- [?] Source non identifiée
28533570 ### Q135: What distinguishes a spin from a spiral dive? ^t80q135
28543571 
28553572 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q135) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q135)
....@@ -2870,6 +3587,10 @@
28703587 - **Option A** incorrectly identifies the outer wing as stalled.
28713588 - **Options C and D** incorrectly assign speed characteristics — in a spin, speed is roughly constant; in a spiral dive, speed increases rapidly.
28723589 
3590
+
3591
+#### Source
3592
+
3593
+- [?] Source non identifiée
28733594 ### Q136: The longitudinal position of the centre of gravity primarily affects stability around which axis? ^t80q136
28743595 
28753596 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q136) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q136)
....@@ -2894,6 +3615,13 @@
28943615 #### Key Terms
28953616 
28963617 CG = Centre of Gravity
3618
+
3619
+#### Source
3620
+
3621
+- Examen Blanc: [S1S Q5 p.4](Exa%20Blanc%20Série_1_Specifiques.pdf#page=4) (score: 0.22)
3622
+- [QuizVDS Q54](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q54): Answer B
3623
+- PDF Answer: A
3624
+
28973625 ### Q137: Which structural element provides directional stability? ^t80q137
28983626 
28993627 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q137) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q137)
....@@ -2915,6 +3643,10 @@
29153643 - **Option B** (elevator) contributes to pitch stability.
29163644 - **Option D** (differential aileron deflection) reduces adverse yaw but is not a stability feature.
29173645 
3646
+
3647
+#### Source
3648
+
3649
+- [ ] ≈ [[Examen Blanc/Questionnaire toutes branches VV.pdf#page=13|VV Q51 p.13]] (clé: **B**)
29183650 ### Q138: In straight-and-level flight at constant engine power, how does the wing's angle of attack compare to that in a climb? ^t80q138
29193651 
29203652 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q138) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q138)
....@@ -2940,6 +3672,10 @@
29403672 #### Key Terms
29413673 
29423674 AoA = Angle of Attack
3675
+
3676
+#### Source
3677
+
3678
+- [?] Source non identifiée
29433679 ### Q139: What is one function of the horizontal tail? ^t80q139
29443680 
29453681 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q139) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q139)
....@@ -2960,6 +3696,13 @@
29603696 - **Option B** is wrong because turns around the vertical axis are initiated by the rudder.
29613697 - **Option C** is incorrect because vertical axis stability comes from the vertical tail.
29623698 - **Option D** is wrong because longitudinal axis (roll) stability is provided by wing dihedral and sweep.
3699
+
3700
+
3701
+#### Source
3702
+
3703
+- Examen Blanc: [S1S Q5 p.4](Exa%20Blanc%20Série_1_Specifiques.pdf#page=4) (score: 0.22)
3704
+- [QuizVDS Q60](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q60): Answer B
3705
+- PDF Answer: A
29633706 
29643707 ### Q140: What happens when the rudder is deflected to the left? ^t80q140
29653708 
....@@ -2983,6 +3726,10 @@
29833726 - **Options A and C** are wrong because pitching is a nose-up/nose-down motion controlled by the elevator, not the rudder.
29843727 - **Option B** reverses the yaw direction — left rudder produces left yaw.
29853728 
3729
+
3730
+#### Source
3731
+
3732
+- [?] Source non identifiée
29863733 ### Q141: Differential aileron deflection is employed to ^t80q141
29873734 
29883735 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q141) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q141)
....@@ -3007,6 +3754,10 @@
30073754 #### Key Terms
30083755 
30093756 AoA = Angle of Attack
3757
+
3758
+#### Source
3759
+
3760
+- [?] Source non identifiée
30103761 ### Q142: How is the force balance affected during a banked turn? ^t80q142
30113762 
30123763 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q142) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q142)
....@@ -3032,6 +3783,10 @@
30323783 
30333784 - **n** — Load Factor (ratio of lift to weight: n = L/W)
30343785 - **D** — Drag
3786
+
3787
+#### Source
3788
+
3789
+- [?] Source non identifiée
30353790 ### Q143: On a Touring Motor Glider (TMG), which engine arrangement produces the least drag? ^t80q143
30363791 
30373792 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q143) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q143)
....@@ -3054,6 +3809,10 @@
30543809 #### Key Terms
30553810 
30563811 TMG = Touring Motor Glider
3812
+
3813
+#### Source
3814
+
3815
+- [?] Source non identifiée
30573816 ### Q144: What effect is known as "adverse yaw"? ^t80q144
30583817 
30593818 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q144) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q144)
....@@ -3075,6 +3834,10 @@
30753834 - **Option B** describes a secondary effect of rudder, not the primary adverse yaw phenomenon.
30763835 - **Option D** incorrectly attributes the extra drag to the up-deflected aileron, when in fact it is the down-deflected aileron that produces more drag.
30773836 
3837
+
3838
+#### Source
3839
+
3840
+- [?] Source non identifiée
30783841 ### Q145: What is the "ground effect"? ^t80q145
30793842 
30803843 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q145) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q145)
....@@ -3098,6 +3861,10 @@
30983861 - **Option D** incorrectly states induced drag increases.
30993862 - Pilots experience ground effect as a floating sensation during the landing flare.
31003863 
3864
+
3865
+#### Source
3866
+
3867
+- [?] Source non identifiée
31013868 ### Q146: Rudder deflections rotate the aircraft around the ^t80q146
31023869 
31033870 ![](figures/Anatomy_sailplane_EN.png)
....@@ -3120,6 +3887,12 @@
31203887 - **Option A** is wrong because the longitudinal axis governs roll, controlled by ailerons.
31213888 - **Option B** is not a standard aeronautical axis designation.
31223889 - **Option C** is wrong because the lateral axis governs pitch, controlled by the elevator.
3890
+
3891
+
3892
+#### Source
3893
+
3894
+- Examen Blanc: [VV Q40 p.219](Questionnaire%20toutes%20branches%20VV.pdf#page=219) (score: 0.26)
3895
+- PDF Answer: C
31233896 
31243897 ### Q147: Which of the following factors causes the load factor to increase during cruise flight? ^t80q147
31253898 
....@@ -3145,6 +3918,13 @@
31453918 #### Key Terms
31463919 
31473920 CG = Centre of Gravity
3921
+
3922
+#### Source
3923
+
3924
+- Examen Blanc: [VV Q66 p.225](Questionnaire%20toutes%20branches%20VV.pdf#page=225) (score: 0.21)
3925
+- [QuizVDS Q74](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q74): Answer D
3926
+- PDF Answer: A
3927
+
31483928 ### Q148: While approaching the next updraft, the variometer shows 3 m/s descent. You expect a mean climb rate of 2 m/s in the thermal. How should you set the McCready ring? ^t80q148
31493929 
31503930 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q148) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q148)
....@@ -3166,6 +3946,10 @@
31663946 - **Option B** sets the ring to zero, which would give a minimum-sink rather than optimal cruise speed.
31673947 - **Option D** erroneously adds the sink rate and climb rate together, which is not how McCready theory works.
31683948 
3949
+
3950
+#### Source
3951
+
3952
+- [?] Source non identifiée
31693953 ### Q149: What must be considered when flying a sailplane equipped with camber flaps? ^t80q149
31703954 
31713955 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q149) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q149)
....@@ -3190,6 +3974,10 @@
31903974 #### Key Terms
31913975 
31923976 D — Drag
3977
+
3978
+#### Source
3979
+
3980
+- [?] Source non identifiée
31933981 ### Q150: On the aerofoil diagram, what does point number 3 represent? ^t80q150
31943982 
31953983 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q150) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q150)
....@@ -3213,6 +4001,10 @@
32134001 - **Option B** (centre of pressure) is not a boundary layer feature but a force application point.
32144002 - **Option C** (stagnation point) is at the leading edge, where flow velocity is zero.
32154003 
4004
+
4005
+#### Source
4006
+
4007
+- [?] Source non identifiée
32164008 ### Q151: In the diagram, what does number 2 correspond to? ^t80q151
32174009 
32184010 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q151) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q151)
....@@ -3234,6 +4026,12 @@
32344026 
32354027 - **Option A** (angle of attack) is an angular measurement, not a line on the diagram.
32364028 - **Option B** (profile thickness) is the perpendicular distance between the upper and lower surfaces, not a straight reference line.
4029
+
4030
+
4031
+#### Source
4032
+
4033
+- Examen Blanc: [S1S Q9 p.41](Exa%20Blanc%20Série_1_Specifiques.pdf#page=41) (score: 0.21)
4034
+- PDF Answer: D
32374035 
32384036 ### Q152: In the figure, the angle (alpha) is referred to as ^t80q152
32394037 
....@@ -3258,6 +4056,10 @@
32584056 - **Option B** (angle of incidence) is the fixed structural angle between the chord line and the aircraft's longitudinal axis, set during manufacturing.
32594057 - **Option D** (lift angle) is not a recognized aviation term.
32604058 
4059
+
4060
+#### Source
4061
+
4062
+- [?] Source non identifiée
32614063 ### Q153: If the right aileron deflects upward and the left aileron deflects downward, how does the aircraft react? ^t80q153
32624064 
32634065 ![](figures/Anatomy_sailplane_EN.png)
....@@ -3279,6 +4081,13 @@
32794081 
32804082 - **Options C and D** incorrectly identify a leftward roll.
32814083 - **Option B** states yaw to the right, but adverse yaw always opposes the roll direction.
4084
+
4085
+
4086
+#### Source
4087
+
4088
+- Examen Blanc: [VV Q41 p.219](Questionnaire%20toutes%20branches%20VV.pdf#page=219) (score: 0.29)
4089
+- [QuizVDS Q68](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q68): Answer B
4090
+- PDF Answer: A
32824091 
32834092 ### Q154: What must be taken into account when flying a sailplane with water ballast? ^t80q154
32844093 
....@@ -3304,6 +4113,10 @@
33044113 #### Key Terms
33054114 
33064115 CG = Centre of Gravity
4116
+
4117
+#### Source
4118
+
4119
+- [?] Source non identifiée
33074120 ### Q155: Which description characterises static stability? ^t80q155
33084121 
33094122 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q155) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q155)
....@@ -3325,6 +4138,10 @@
33254138 - **Option B** describes neutral stability, where the aircraft stays wherever it is displaced.
33264139 - **Option C** describes static instability, where the aircraft diverges further from equilibrium.
33274140 
4141
+
4142
+#### Source
4143
+
4144
+- [?] Source non identifiée
33284145 ### Q156: How do the best gliding angle and best glide speed change when a sailplane carries water ballast compared to flying without it? ^t80q156
33294146 
33304147 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q156) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q156)
....@@ -3346,6 +4163,10 @@
33464163 
33474164 - **Options C and D** incorrectly state that best glide speed decreases.
33484165 
4166
+
4167
+#### Source
4168
+
4169
+- [?] Source non identifiée
33494170 ### Q157: Which constructive feature is designed to reduce control forces? ^t80q157
33504171 
33514172 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q157) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q157)
....@@ -3367,6 +4188,10 @@
33674188 - **Option B** (vortex generators) energise the boundary layer to delay flow separation.
33684189 - **Option D** (differential aileron deflection) reduces adverse yaw, not control forces.
33694190 
4191
+
4192
+#### Source
4193
+
4194
+- [?] Source non identifiée
33704195 ### Q158: When any body of arbitrary shape is surrounded by airflow (v > 0), it always produces ^t80q158
33714196 
33724197 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q158) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q158)
....@@ -3391,6 +4216,12 @@
33914216 #### Key Terms
33924217 
33934218 D — Drag
4219
+
4220
+#### Source
4221
+
4222
+- Examen Blanc: [S3 Q2 p.37](Exa%20Blanc%20Série_3.pdf#page=37) (score: 0.23)
4223
+- [QuizVDS Q9](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q9): Answer B
4224
+
33944225 ### Q159: "Longitudinal stability" refers to stability around which axis? ^t80q159
33954226 
33964227 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q159) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q159)
....@@ -3411,6 +4242,13 @@
34114242 - **Option A** (vertical axis) governs directional/yaw stability.
34124243 - **Option B** (propeller axis) is not a standard stability axis.
34134244 - **Option C** (longitudinal axis) governs roll/lateral stability.
4245
+
4246
+
4247
+#### Source
4248
+
4249
+- Examen Blanc: [S1S Q5 p.4](Exa%20Blanc%20Série_1_Specifiques.pdf#page=4) (score: 0.25)
4250
+- [QuizVDS Q53](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q53): Answer A
4251
+- PDF Answer: A
34144252 
34154253 ### Q160: What does "wing loading" mean? ^t80q160
34164254 
....@@ -3436,6 +4274,10 @@
34364274 #### Key Terms
34374275 
34384276 D — Drag
4277
+
4278
+#### Source
4279
+
4280
+- [?] Source non identifiée
34394281 ### Q161: What phenomenon is known as adverse yaw? ^t80q161
34404282 
34414283 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q161) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q161)
....@@ -3457,6 +4299,10 @@
34574299 - **Option B** describes a secondary rudder-roll coupling, not the primary adverse yaw effect.
34584300 - **Option C** incorrectly attributes the drag increase to the up-deflected aileron; in reality, it is the down-deflected aileron that creates more drag.
34594301 
4302
+
4303
+#### Source
4304
+
4305
+- [?] Source non identifiée
34604306 ### Q162: What is the "ground effect"? ^t80q162
34614307 
34624308 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q162) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q162)
....@@ -3475,6 +4321,12 @@
34754321 In ground effect (within approximately one wingspan of the surface), the ground physically constrains wingtip vortex development, reducing downwash. This increases the effective angle of attack (raising lift) while simultaneously reducing induced drag. Pilots notice this as a floating sensation during the landing flare.
34764322 
34774323 - **Options A, B, and C** all incorrectly describe the lift-drag relationship — the correct combination is increased lift with decreased induced drag.
4324
+
4325
+
4326
+#### Source
4327
+
4328
+- Examen Blanc: [S2 Q18 p.27](Exa%20Blanc%20Série_2.pdf#page=27) (score: 0.26)
4329
+- [QuizVDS Q90](../../Examen%20Blanc/QuizVDS/80%20-%20Principles%20of%20Flight.md#^q90): Answer B
34784330 
34794331 ### Q163: Does air density affect the minimum speed (IAS) of a glider? ^t80q163
34804332 
....@@ -3499,6 +4351,12 @@
34994351 - **TAS** = True Airspeed
35004352 - **CL_max** = Maximum lift coefficient before stall
35014353 
4354
+
4355
+#### Source
4356
+
4357
+- Examen Blanc: [VV Q57 p.223](Questionnaire%20toutes%20branches%20VV.pdf#page=223) (score: 0.92)
4358
+- PDF Answer: C
4359
+
35024360 ### Q164: In which speed range can vibrations and flutter occur? ^t80q164
35034361 
35044362 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q164) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q164)
....@@ -3522,6 +4380,12 @@
35224380 - **Va** = Manoeuvring Speed
35234381 - **Vs** = Stall Speed
35244382 
4383
+
4384
+#### Source
4385
+
4386
+- Examen Blanc: [VV Q27 p.185](Questionnaire%20toutes%20branches%20VV.pdf#page=185) (score: 0.33)
4387
+- PDF Answer: C
4388
+
35254389 ### Q165: Vibrations can occur when ^t80q165
35264390 
35274391 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q165) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q165)
....@@ -3539,6 +4403,12 @@
35394403 
35404404 Excessive play in the mechanical linkages of control surfaces or flaps creates conditions favourable to vibration by reducing structural damping. The play allows surfaces to move freely under aerodynamic forces, potentially generating oscillations. This is one reason why control system play is strictly limited and checked during maintenance inspections. Large amounts of play can lower the flutter onset speed to below Vne.
35414405 
4406
+
4407
+#### Source
4408
+
4409
+- Examen Blanc: [VV Q79 p.227](Questionnaire%20toutes%20branches%20VV.pdf#page=227) (score: 0.58)
4410
+- PDF Answer: A
4411
+
35424412 ### Q166: Vibrations can also occur under which conditions? ^t80q166
35434413 
35444414 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q166) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q166)
....@@ -3555,6 +4425,12 @@
35554425 #### Explanation
35564426 
35574427 Ice on control surfaces alters their mass distribution and thus their mass balance. Mass balancing is designed to position the control surface's centre of mass at or ahead of the hinge axis, preventing flutter. Ice, depositing mainly on leading edges and outer surfaces, can shift the centre of mass behind the hinge and lower the critical flutter speed well below Vne. Flying at high speed with ice-contaminated, unbalanced control surfaces is particularly dangerous.
4428
+
4429
+
4430
+#### Source
4431
+
4432
+- Examen Blanc: [VV Q80 p.228](Questionnaire%20toutes%20branches%20VV.pdf#page=228) (score: 0.56)
4433
+- PDF Answer: C
35584434 
35594435 ### Q167: In which speed range can the maximum load factor be exceeded, leading to structural overload? ^t80q167
35604436 
....@@ -3578,6 +4454,12 @@
35784454 - **Va** = Manoeuvring speed - speed below which full deflections are safe
35794455 - **Vne** = Never exceed speed
35804456 
4457
+
4458
+#### Source
4459
+
4460
+- Examen Blanc: [VV Q81 p.228](Questionnaire%20toutes%20branches%20VV.pdf#page=228) (score: 0.59)
4461
+- PDF Answer: B
4462
+
35814463 ### Q168: Above which speed can abrupt or full control deflections damage the glider's structure? ^t80q168
35824464 
35834465 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q168) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q168)
....@@ -3594,6 +4476,12 @@
35944476 #### Explanation
35954477 
35964478 Manoeuvring speed Va is precisely the speed above which abrupt or full control deflections can produce aerodynamic loads exceeding the aircraft's structural limits. Below Va, the wing stalls before these loads are reached. Above Va, a full deflection can generate enough lift or control surface force to damage spars, wing attachments or the tailplane. Va is therefore the practical limit for energetic manoeuvres and turbulence penetration.
4479
+
4480
+
4481
+#### Source
4482
+
4483
+- Examen Blanc: [VV Q83 p.228](Questionnaire%20toutes%20branches%20VV.pdf#page=228) (score: 0.93)
4484
+- PDF Answer: A
35974485 
35984486 ### Q169: When the maximum load factor is exceeded, what is the primary risk? ^t80q169
35994487 
....@@ -3612,6 +4500,12 @@
36124500 
36134501 The maximum (limit) load factor is the highest load the glider's structure can withstand repeatedly without permanent deformation. Beyond the ultimate factor (typically 1.5 times the limit), structural failure can occur. Exceeding the limit load factor during abrupt manoeuvres or in turbulence can cause deformation or rupture of wing spars, fuselage attachments or control surfaces. Stall and spin are aerodynamic phenomena, not structural ones, and occur at insufficient load factors, not excessive ones.
36144502 
4503
+
4504
+#### Source
4505
+
4506
+- Examen Blanc: [VV Q31 p.186](Questionnaire%20toutes%20branches%20VV.pdf#page=186) (score: 0.53)
4507
+- PDF Answer: C
4508
+
36154509 ### Q170: The mass balance (mass balancing) of an aileron has lost lead weights. What can be the consequence? ^t80q170
36164510 
36174511 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q170) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q170)
....@@ -3629,6 +4523,12 @@
36294523 
36304524 Mass balancing places lead counterweights ahead of the hinge axis to bring the control surface's centre of mass to or ahead of that axis. If these counterweights fall off, the centre of mass shifts aft of the hinge. The control surface then becomes susceptible to flutter - a self-amplifying aeroelastic oscillation in which inertial and aerodynamic forces reinforce each other. This flutter can quickly become divergent and destroy the control surface and airframe. That is why any damage to control surface counterweights requires inspection before the next flight.
36314525 
4526
+
4527
+#### Source
4528
+
4529
+- Examen Blanc: [VV Q85 p.229](Questionnaire%20toutes%20branches%20VV.pdf#page=229) (score: 0.48)
4530
+- PDF Answer: B
4531
+
36324532 ### Q171: What is the danger of flying at minimum speed in turbulent air? ^t80q171
36334533 
36344534 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q171) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q171)
....@@ -3645,6 +4545,12 @@
36454545 #### Explanation
36464546 
36474547 At minimum speed (stall speed), the wing operates at its maximum lift coefficient CL_max with virtually no margin before stall. In turbulent air, upward gusts can suddenly increase the angle of attack beyond the critical angle, causing an instantaneous stall. In addition, speed fluctuations induced by turbulence can momentarily reduce airspeed below Vs. This is why it is particularly dangerous to fly at minimum speed in rough air, especially on final approach during landing.
4548
+
4549
+
4550
+#### Source
4551
+
4552
+- Examen Blanc: [VV Q92 p.230](Questionnaire%20toutes%20branches%20VV.pdf#page=230) (score: 0.79)
4553
+- PDF Answer: C
36484554 
36494555 ### Q172: How does air density change when temperature increases? ^t80q172
36504556 
....@@ -3669,6 +4575,12 @@
36694575 - **R** = gas constant
36704576 - **T** = absolute temperature (Kelvin)
36714577 
4578
+
4579
+#### Source
4580
+
4581
+- Examen Blanc: [VV Q94 p.231](Questionnaire%20toutes%20branches%20VV.pdf#page=231) (score: 0.55)
4582
+- PDF Answer: A
4583
+
36724584 ### Q173: In what proportion does drag change with airspeed? ^t80q173
36734585 
36744586 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q173) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q173)
....@@ -3691,6 +4603,12 @@
36914603 - **q** = dynamic pressure (q = 0.5 x rho x V^2)
36924604 - **V** = airspeed
36934605 
4606
+
4607
+#### Source
4608
+
4609
+- Examen Blanc: [VV Q96 p.231](Questionnaire%20toutes%20branches%20VV.pdf#page=231) (score: 0.33)
4610
+- PDF Answer: D
4611
+
36944612 ### Q174: What is understood by static pressure? ^t80q174
36954613 
36964614 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q174) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q174)
....@@ -3707,6 +4625,12 @@
37074625 #### Explanation
37084626 
37094627 Static pressure is the pressure exerted by the surrounding atmosphere on an object at rest relative to the air. It is measured by static ports (flush orifices on the fuselage, away from airflow disturbance). It decreases with altitude according to the standard atmosphere model. In the Pitot-static system, static pressure is subtracted from total pressure (Pitot) to obtain dynamic pressure, which is proportional to the square of true airspeed - this is the operating principle of the airspeed indicator.
4628
+
4629
+
4630
+#### Source
4631
+
4632
+- Examen Blanc: [VV Q97 p.231](Questionnaire%20toutes%20branches%20VV.pdf#page=231) (score: 0.64)
4633
+- PDF Answer: C
37104634 
37114635 ### Q175: How does the maximum permissible speed Vne of a glider in IAS behave as altitude increases? ^t80q175
37124636 
....@@ -3732,6 +4656,12 @@
37324656 - **TAS** = True Airspeed
37334657 - **AFM** = Aircraft Flight Manual
37344658 
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+
4660
+#### Source
4661
+
4662
+- Examen Blanc: [VV Q20 p.78](Questionnaire%20toutes%20branches%20VV.pdf#page=78) (score: 0.67)
4663
+- PDF Answer: C
4664
+
37354665 ### Q176: In what proportion does lift change when airspeed increases? ^t80q176
37364666 
37374667 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q176) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q176)
....@@ -3749,6 +4679,12 @@
37494679 
37504680 Lift L = CL x 0.5 x rho x V^2 x S. At constant angle of attack and density, lift is proportional to V^2. If speed doubles, lift quadruples. This property allows flight at high speed with a lower angle of attack - the lift generated scales with the square of speed. It also explains why stall speeds increase with the square root of the load factor: in a turn, more lift is required, demanding a higher speed to avoid stalling.
37514681 
4682
+
4683
+#### Source
4684
+
4685
+- Examen Blanc: [VV Q104 p.233](Questionnaire%20toutes%20branches%20VV.pdf#page=233) (score: 0.23)
4686
+- PDF Answer: B
4687
+
37524688 ### Q177: Which statement is FALSE regarding the relationship between lift/drag and airspeed? ^t80q177
37534689 
37544690 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q177) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q177)
....@@ -3765,6 +4701,12 @@
37654701 #### Explanation
37664702 
37674703 The FALSE statement is C. Neither lift nor drag varies linearly with speed - both vary as the square of speed (proportionally to dynamic pressure q = 0.5 x rho x V^2). Doubling speed quadruples both lift AND drag (at constant angle of attack). Statements A, B and D are correct: lift does increase with speed, drag does vary with speed, and lift does depend on angle of attack via the lift coefficient CL.
4704
+
4705
+
4706
+#### Source
4707
+
4708
+- Examen Blanc: [VV Q105 p.233](Questionnaire%20toutes%20branches%20VV.pdf#page=233) (score: 0.63)
4709
+- PDF Answer: C
37684710 
37694711 ### Q178: What is understood by total pressure? ^t80q178
37704712 
....@@ -3788,3 +4730,9 @@
37884730 - **Dynamic pressure** = 0.5 x rho x V^2
37894731 - **Static pressure** = ambient atmospheric pressure
37904732 - **Total pressure** = static pressure + dynamic pressure
4733
+
4734
+
4735
+#### Source
4736
+
4737
+- Examen Blanc: [VV Q106 p.233](Questionnaire%20toutes%20branches%20VV.pdf#page=233) (score: 0.83)
4738
+- PDF Answer: C