From a3f8f79b018d166cecb3f5c9869357194b872a94 Mon Sep 17 00:00:00 2001 From: Matthias Nott <mnott@mnsoft.org> Date: Sun, 22 Mar 2026 12:52:17 +0100 Subject: [PATCH] feat: bulletized key terms, formula variables, airspace charts, expanded explanations --- SPL Exam Questions EN/80 - Principles of Flight.md | 321 +++++++++++++++++++++++++++++++++------------------- 1 files changed, 203 insertions(+), 118 deletions(-) diff --git a/SPL Exam Questions EN/80 - Principles of Flight.md b/SPL Exam Questions EN/80 - Principles of Flight.md index 126f7ba..e605f2c 100644 --- a/SPL Exam Questions EN/80 - Principles of Flight.md +++ b/SPL Exam Questions EN/80 - Principles of Flight.md @@ -38,8 +38,12 @@ #### Key Terms -VS = Stall Speed - +- **VS** = Stall Speed +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **rho** — ρ (rho) — air density +- **S** — Wing Area — total planform area of the wings +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) +- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q3: After one wing stalls and the nose drops, what is the correct technique to prevent a spin? ^t80q3 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q3) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q3) @@ -59,8 +63,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q4: Which component is responsible for pitch stabilisation during cruise? ^t80q4 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q4) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q4) @@ -80,8 +83,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q5: What can happen when the never-exceed speed (VNE) is surpassed in flight? ^t80q5 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q5) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q5) @@ -101,8 +103,7 @@ #### Key Terms -VNE = Never Exceed Speed - +- **VNE** = Never Exceed Speed ### Q6: What effect does a rearward centre of gravity position have on a glider's handling? ^t80q6 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q6) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q6) @@ -122,8 +123,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q7: What purpose does the vertical tail fin (rudder assembly) serve? ^t80q7 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q7) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q7) @@ -158,6 +158,10 @@ In a level coordinated turn, the load factor n = 1/cos(bank angle). At 60° bank, n = 1/cos(60°) = 1/0.5 = 2.0. This means the effective weight the wings must support doubles. Stall speed increases by a factor of √n = √2 ≈ 1.41, i.e. a 41% increase. This is why steep turns at low altitude are dangerous for gliders — the stall margin shrinks dramatically. +#### Key Terms + +- **n** — Load Factor (ratio of lift to weight: n = L/W) + ### Q9: What is the relationship between aspect ratio and induced drag? ^t80q9 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q9) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q9) @@ -174,6 +178,13 @@ #### Explanation Induced drag is inversely proportional to aspect ratio (AR): D_induced ∝ CL² / (π × AR × e). A longer, narrower wing (high AR) produces the same lift with weaker wingtip vortices and therefore less induced drag. This is why gliders have very high aspect ratios — it is the primary design feature that maximises the lift-to-drag ratio and glide performance. + +#### Key Terms + +- **D_induced** — Induced Drag — drag created as a by-product of generating lift +- **AR** — Aspect Ratio — ratio of wingspan² to wing area +- **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution) +- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q10: When the elevator trim tab is deflected downward, what is the resulting pitch tendency? ^t80q10 @@ -209,6 +220,10 @@ The glider's speed polar plots the vertical sink rate (Vz, typically in m/s) against the horizontal airspeed (Vh). It is the fundamental performance diagram for a glider: it reveals the minimum sink speed (the lowest point on the curve), the best glide speed (given by the tangent from the origin), and inter-thermal cruise speeds (McCready tangents). All cross-country speed-to-fly decisions are based on this curve. +#### Key Terms + +- **m** — mass of the aircraft + ### Q12: In straight and level flight, what happens to the required angle of attack as speed increases? ^t80q12 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q12) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q12) @@ -228,8 +243,11 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient +- **ρ** (rho) — air density +- **L** — Lift — aerodynamic force acting perpendicular to the airflow +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) +- **S** — Wing Area — total planform area of the wings ### Q13: What is the function of wing fences or boundary layer fences? ^t80q13 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q13) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q13) @@ -300,8 +318,11 @@ #### Key Terms -IAS = Indicated Airspeed; TAS = True Airspeed - +- **IAS** = Indicated Airspeed +- **TAS** = True Airspeed +- **ρ₀** — air density at sea level (ISA: 1.225 kg/m³) +- **ρ** (rho) — air density +- **q** — dynamic pressure (q = ½ × ρ × V²) ### Q17: What does the term "load factor" describe? ^t80q17 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q17) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q17) @@ -318,6 +339,13 @@ #### Explanation Load factor (n) is defined as the ratio of the lift generated by the wings to the aircraft's weight: n = L/W. In straight and level flight, n = 1. In a turn, n > 1 because extra lift is needed for the centripetal force. In a vertical pullup, n can exceed the design limits. The structural design of the glider is rated for specific load factor limits (typically +5.3g / -2.65g for utility category). + +#### Key Terms + +- **L** — Lift — aerodynamic force acting perpendicular to the airflow +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) +- **n** — Load Factor (ratio of lift to weight: n = L/W) +- **g** — gravitational acceleration (9.81 m/s²) ### Q18: How does increasing aircraft weight affect the best glide ratio? ^t80q18 @@ -389,8 +417,7 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient ### Q22: What is the primary function of an elevator trim tab? ^t80q22 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q22) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q22) @@ -425,6 +452,10 @@ In a turn, the load factor n = 1/cos(bank angle) exceeds 1, meaning the wings must generate more lift than in straight flight. The stall speed increases by the factor √n. At 45° bank, stall speed increases by 19%; at 60° bank by 41%. This is a critical safety consideration when thermalling near the ground — the steeper the bank, the closer the pilot is to the elevated stall speed. +#### Key Terms + +- **n** — Load Factor (ratio of lift to weight: n = L/W) + ### Q24: What is the centre of pressure of an aerofoil? ^t80q24 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q24) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q24) @@ -444,8 +475,8 @@ #### Key Terms -AoA = Angle of Attack; CG = Centre of Gravity - +- **AoA** = Angle of Attack +- **CG** = Centre of Gravity ### Q25: At what point during flight is parasite drag greatest? ^t80q25 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q25) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q25) @@ -465,8 +496,7 @@ #### Key Terms -VNE = Never Exceed Speed - +- **VNE** = Never Exceed Speed ### Q26: What is the Bernoulli principle as applied to an aerofoil? ^t80q26 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q26) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q26) @@ -520,8 +550,7 @@ #### Key Terms -AGL = Above Ground Level - +- **AGL** = Above Ground Level ### Q29: What does the term "washout" refer to in wing design? ^t80q29 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q29) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q29) @@ -558,8 +587,9 @@ #### Key Terms -AoA = Angle of Attack; CL = Lift Coefficient - +- **AoA** = Angle of Attack +- **CL** = Lift Coefficient +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling ### Q31: How does the flap position affect the stall speed? ^t80q31 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q31) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q31) @@ -579,8 +609,12 @@ #### Key Terms -VS = Stall Speed - +- **VS** = Stall Speed +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **ρ** (rho) — air density +- **S** — Wing Area — total planform area of the wings +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) +- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q32: What is the purpose of a laminar-flow aerofoil? ^t80q32 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q32) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q32) @@ -617,8 +651,8 @@ #### Key Terms -IAS = Indicated Airspeed; TAS = True Airspeed - +- **IAS** = Indicated Airspeed +- **TAS** = True Airspeed ### Q34: What is the difference between static stability and dynamic stability? ^t80q34 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q34) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q34) @@ -672,8 +706,7 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient ### Q37: In which direction does the centre of pressure move as the angle of attack increases (pre-stall)? ^t80q37 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q37) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q37) @@ -693,8 +726,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q38: What determines the critical angle of attack at which a wing stalls? ^t80q38 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q38) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q38) @@ -728,6 +760,16 @@ #### Explanation Induced drag decreases monotonically with increasing airspeed in level flight: D_induced = 2W^2 / (rho * V^2 * S^2 * pi * AR * e). As V increases, induced drag continuously falls — there is no minimum/maximum within the normal flight envelope. Parasite drag (not induced drag) has the U-shaped curve described in B/C. Total drag has a minimum at the speed where induced drag equals parasite drag; induced drag itself simply decreases with speed. + +#### Key Terms + +- **D_induced** — Induced Drag — drag created as a by-product of generating lift +- **rho** — ρ (rho) — air density +- **AR** — Aspect Ratio — ratio of wingspan² to wing area +- **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution) +- **S** — Wing Area — total planform area of the wings +- **V** — Velocity / Airspeed +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) ### Q40: Which types of drag make up total drag? ^t80q40 @@ -768,8 +810,9 @@ #### Key Terms -AoA = Angle of Attack; CD = Drag Coefficient; CL = Lift Coefficient - +- **AoA** = Angle of Attack +- **CD** = Drag Coefficient +- **CL** = Lift Coefficient ### Q42: To recover from a stall, it is essential to ^t80q42 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q42) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q42) @@ -789,8 +832,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q43: During a stall, how do lift and drag behave? ^t80q43 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q43) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q43) @@ -810,8 +852,10 @@ #### Key Terms -AoA = Angle of Attack; CD = Drag Coefficient; CL = Lift Coefficient - +- **AoA** = Angle of Attack +- **CD** = Drag Coefficient +- **CL** = Lift Coefficient +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling ### Q44: The critical angle of attack ^t80q44 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q44) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q44) @@ -831,8 +875,13 @@ #### Key Terms -AoA = Angle of Attack; VS = Stall Speed - +- **AoA** = Angle of Attack +- **VS** = Stall Speed +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **rho** — ρ (rho) — air density +- **S** — Wing Area — total planform area of the wings +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) +- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q45: What leads to a lower stall speed Vs (IAS)? ^t80q45 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q45) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q45) @@ -852,8 +901,16 @@ #### Key Terms -IAS = Indicated Airspeed; TAS = True Airspeed; VS = Stall Speed - +- **IAS** = Indicated Airspeed +- **TAS** = True Airspeed +- **VS** = Stall Speed +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **rho** — ρ (rho) — air density +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) +- **S** — Wing Area — total planform area of the wings +- **n** — Load Factor (ratio of lift to weight: n = L/W) +- **q** — dynamic pressure (q = ½ × ρ × V²) +- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q46: Which statement about a spin is correct? ^t80q46 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q46) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q46) @@ -873,8 +930,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q47: The laminar boundary layer on the aerofoil lies between ^t80q47 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q47) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q47) @@ -962,8 +1018,7 @@ #### Key Terms -ISA = International Standard Atmosphere - +- **ISA** = International Standard Atmosphere ### Q52: During a sideslip, the permitted flap position is ^t80q52 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q52) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q52) @@ -1034,8 +1089,8 @@ #### Key Terms -ICAO = International Civil Aviation Organization; ISA = International Standard Atmosphere - +- **ICAO** = International Civil Aviation Organization +- **ISA** = International Standard Atmosphere ### Q56: At approximately what altitude does atmospheric pressure fall to half its sea-level value? ^t80q56 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q56) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q56) @@ -1055,8 +1110,7 @@ #### Key Terms -ICAO = International Civil Aviation Organization - +- **ICAO** = International Civil Aviation Organization ### Q57: Density altitude always corresponds to ^t80q57 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q57) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q57) @@ -1076,8 +1130,8 @@ #### Key Terms -ISA = International Standard Atmosphere; QNH = Pressure adjusted to mean sea level - +- **ISA** = International Standard Atmosphere +- **QNH** = Pressure adjusted to mean sea level ### 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 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q58) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q58) @@ -1094,6 +1148,11 @@ #### Explanation The continuity equation states that for an incompressible fluid, the volumetric flow rate Q = S × V is constant along a streamtube. If the cross-section S decreases, the velocity V must increase proportionally to keep Q constant. This principle, combined with Bernoulli's theorem, explains why air accelerates over the curved upper surface of an aerofoil, creating a low-pressure region that generates lift. + +#### Key Terms + +- **S** — Wing Area — total planform area of the wings +- **V** — Velocity / Airspeed ### Q59: The aerodynamic resultant (drag and lift) depends on air density. When air density decreases ^t80q59 @@ -1114,8 +1173,9 @@ #### Key Terms -TAS = True Airspeed - +- **TAS** = True Airspeed +- **ρ** (rho) — air density +- **q** — dynamic pressure (q = ½ × ρ × V²) ### 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 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q60) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q60) @@ -1135,8 +1195,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q61: The angle between the aerofoil chord line and the aircraft's longitudinal axis is called ^t80q61 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q61) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q61) @@ -1224,8 +1283,11 @@ #### Key Terms -CD = Drag Coefficient - +- **CD** = Drag Coefficient +- **ρ** (rho) — air density +- **S** — Wing Area — total planform area of the wings +- **q** — dynamic pressure (q = ½ × ρ × V²) +- **D** — Drag ### Q66: On the speed polar, which tangent touches the curve at the point of minimum sink rate? ^t80q66 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q66) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q66) @@ -1273,8 +1335,12 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient +- **D_induced** — Induced Drag — drag created as a by-product of generating lift +- **AR** — Aspect Ratio — ratio of wingspan² to wing area +- **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution) +- **S** — Wing Area — total planform area of the wings +- **q** — dynamic pressure (q = ½ × ρ × V²) ### Q68: How does the minimum speed of an aircraft in a level turn at 45-degree bank compare to straight-and-level flight? ^t80q68 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q68) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q68) @@ -1294,8 +1360,8 @@ #### Key Terms -VS = Stall Speed - +- **VS** = Stall Speed +- **n** — Load Factor (ratio of lift to weight: n = L/W) ### Q69: Adverse yaw is caused by ^t80q69 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q69) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q69) @@ -1332,8 +1398,9 @@ #### Key Terms -CAS = Calibrated Airspeed; IAS = Indicated Airspeed; TAS = True Airspeed - +- **CAS** = Calibrated Airspeed +- **IAS** = Indicated Airspeed +- **TAS** = True Airspeed ### Q71: The speed range authorised for the use of slotted flaps is: ^t80q71 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q71) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q71) @@ -1353,8 +1420,7 @@ #### Key Terms -VA = Manoeuvring Speed - +- **VA** = Manoeuvring Speed ### Q72: Wing tip vortices are caused by pressure equalisation from: ^t80q72 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q72) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q72) @@ -1408,8 +1474,7 @@ #### Key Terms -ICAO = International Civil Aviation Organization - +- **ICAO** = International Civil Aviation Organization ### Q75: Regarding airflow, the simplified continuity equation states: At the same moment, the same mass of air passes through different cross-sections. Therefore: ^t80q75 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q75) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q75) @@ -1499,8 +1564,7 @@ #### Key Terms -ISA = International Standard Atmosphere - +- **ISA** = International Standard Atmosphere ### Q80: The speed displayed on the airspeed indicator (ASI) is a measurement of: ^t80q80 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q80) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q80) @@ -1554,8 +1618,7 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient ### Q83: The aerodynamic centre of an aerofoil in an airflow is the point of application of: ^t80q83 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q83) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q83) @@ -1609,8 +1672,7 @@ #### Key Terms -TAS = True Airspeed - +- **TAS** = True Airspeed ### Q86: Yaw stability of an aircraft is provided by: ^t80q86 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q86) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q86) @@ -1681,6 +1743,10 @@ Aerodynamic drag depends notably on air density (ρ), since F_D = Cd × 0.5 × ρ × v² × A. The body's own density, chemical composition, and mass do not directly affect aerodynamic drag. +#### Key Terms + +- **ρ** (rho) — air density + ### Q90: In the drawing below, the aerofoil chord is represented by: ^t80q90 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q90) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q90) @@ -1723,8 +1789,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q92: Given equal frontal area and equal airflow speed, what determines the drag of a body? ^t80q92 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q92) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q92) @@ -1747,8 +1812,10 @@ #### Key Terms -CD = Drag Coefficient - +- **CD** = Drag Coefficient +- **rho** — ρ (rho) — air density +- **S** — Wing Area — total planform area of the wings +- **D** — Drag ### Q93: What is the origin of induced drag on a wing? ^t80q93 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q93) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q93) @@ -1793,8 +1860,8 @@ #### Key Terms -ICAO = International Civil Aviation Organization; ISA = International Standard Atmosphere - +- **ICAO** = International Civil Aviation Organization +- **ISA** = International Standard Atmosphere ### Q95: In the aerofoil diagram below, which line represents the mean camber line? ^t80q95 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q95) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q95) @@ -1860,8 +1927,8 @@ #### Key Terms -AoA = Angle of Attack; VNE = Never Exceed Speed - +- **AoA** = Angle of Attack +- **VNE** = Never Exceed Speed ### Q98: At what condition does airflow separation from an aerofoil occur? ^t80q98 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q98) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q98) @@ -1885,8 +1952,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q99: What is the mean gravitational acceleration at the surface of the Earth? ^t80q99 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q99) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q99) @@ -1910,8 +1976,7 @@ #### Key Terms -ISA = International Standard Atmosphere - +- **ISA** = International Standard Atmosphere ### Q100: True Airspeed (TAS) is obtained from the airspeed indicator (ASI) reading by: ^t80q100 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q100) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q100) @@ -1935,8 +2000,10 @@ #### Key Terms -CAS = Calibrated Airspeed; IAS = Indicated Airspeed; ISA = International Standard Atmosphere; TAS = True Airspeed - +- **CAS** = Calibrated Airspeed +- **IAS** = Indicated Airspeed +- **ISA** = International Standard Atmosphere +- **TAS** = True Airspeed ### Q101: A shift of the centre of gravity is caused by: ^t80q101 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q101) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q101) @@ -1960,8 +2027,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q102: The high-lift device shown in the diagram is a: ^t80q102 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q102) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q102) @@ -2028,8 +2094,7 @@ #### Key Terms -ICAO = International Civil Aviation Organization - +- **ICAO** = International Civil Aviation Organization ### Q105: The airspeed indicator (ASI) reading is based on a measurement of: ^t80q105 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q105) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q105) @@ -2050,6 +2115,12 @@ - **Option A** is nonsensical — a weathervane measures wind direction, not pressure. - **Option C** is wrong because measuring only total pressure without subtracting static pressure gives no speed information. - **Option D** is also incorrect because static pressure alone tells you only about altitude, not airspeed. + +#### Key Terms + +- **rho** — ρ (rho) — air density +- **q** — dynamic pressure (q = ½ × ρ × V²) +- **D** — Drag ### Q106: Roll stability is influenced by: ^t80q106 @@ -2095,8 +2166,8 @@ #### Key Terms -VA = Manoeuvring Speed; VNE = Never Exceed Speed - +- **VA** = Manoeuvring Speed +- **VNE** = Never Exceed Speed ### Q108: When the wing's angle of incidence is larger at the root than at the tip, this is called: ^t80q108 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q108) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q108) @@ -2117,6 +2188,10 @@ - **Option A** (aspect ratio) is the span-to-chord ratio. - **Option B** (aerodynamic twist) achieves a similar stall progression by using different aerofoil profiles along the span rather than physical twist. - **Option D** (interference compensation) is not a standard aerodynamic term for wing twist. + +#### Key Terms + +- **D** — Drag ### Q109: Barometric pressure in the Earth's atmosphere has the characteristic of: ^t80q109 @@ -2335,8 +2410,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q119: What benefit does differential aileron deflection provide? ^t80q119 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q119) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q119) @@ -2444,8 +2518,8 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling ### Q124: In a coordinated turn, what is the relationship between load factor (n) and stall speed (Vs)? ^t80q124 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q124) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q124) @@ -2468,8 +2542,9 @@ #### Key Terms -VS = Stall Speed - +- **VS** = Stall Speed +- **n** — Load Factor (ratio of lift to weight: n = L/W) +- **D** — Drag ### Q125: The pressure equalisation between the upper and lower wing surfaces results in ^t80q125 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q125) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q125) @@ -2534,8 +2609,8 @@ #### Key Terms -CD = Drag Coefficient; CL = Lift Coefficient - +- **CD** = Drag Coefficient +- **CL** = Lift Coefficient ### Q128: Any arbitrarily shaped body placed in an airflow (v > 0) always produces ^t80q128 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q128) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q128) @@ -2647,8 +2722,8 @@ #### Key Terms -CL = Lift Coefficient - +- **CL** = Lift Coefficient +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling ### Q133: What is the aerodynamic effect of deploying airbrakes? ^t80q133 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q133) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q133) @@ -2693,8 +2768,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q135: What distinguishes a spin from a spiral dive? ^t80q135 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q135) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q135) @@ -2738,8 +2812,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q137: Which structural element provides directional stability? ^t80q137 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q137) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q137) @@ -2785,8 +2858,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q139: What is one function of the horizontal tail? ^t80q139 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q139) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q139) @@ -2851,8 +2923,7 @@ #### Key Terms -AoA = Angle of Attack - +- **AoA** = Angle of Attack ### Q142: How is the force balance affected during a banked turn? ^t80q142 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q142) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q142) @@ -2873,6 +2944,11 @@ - **Option A** is wrong because more, not less, lift is needed. - **Option B** is imprecise — from the aircraft's reference frame it appears as centrifugal force, but the actual physics involves centripetal force. - **Option D** does not fully describe the force balance requirement. + +#### Key Terms + +- **n** — Load Factor (ratio of lift to weight: n = L/W) +- **D** — Drag ### Q143: On a Touring Motor Glider (TMG), which engine arrangement produces the least drag? ^t80q143 @@ -2895,8 +2971,7 @@ #### Key Terms -TMG = Touring Motor Glider - +- **TMG** = Touring Motor Glider ### Q144: What effect is known as "adverse yaw"? ^t80q144 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q144) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q144) @@ -2985,8 +3060,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### 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 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q148) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q148) @@ -3028,6 +3102,10 @@ - **Option A** is not universally correct — winch launch flap settings vary by type. - **Option B** reverses the restriction. - **Option D** is wrong because negative camber is a cruise setting, not appropriate for the high-lift-demand winch launch phase. + +#### Key Terms + +- **D** — Drag ### Q150: On the aerofoil diagram, what does point number 3 represent? ^t80q150 @@ -3140,8 +3218,7 @@ #### Key Terms -CG = Centre of Gravity - +- **CG** = Centre of Gravity ### Q155: Which description characterises static stability? ^t80q155 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q155) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q155) @@ -3226,6 +3303,10 @@ - **Option C** is incorrect because drag increases with V² — it is not constant. - **Option D** is physically impossible — drag-free flight does not exist in a real fluid. +#### Key Terms + +- **D** — Drag + ### Q159: "Longitudinal stability" refers to stability around which axis? ^t80q159 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q159) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q159) @@ -3268,6 +3349,10 @@ - **Option C** (drag per weight) describes a drag-to-weight ratio. - **Option D** (wing area per weight) is the mathematical inverse of wing loading. +#### Key Terms + +- **D** — Drag + ### Q161: What phenomenon is known as adverse yaw? ^t80q161 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q161) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q161) -- Gitblit v1.3.1