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Matthias Nott
2026-03-22 a3f8f79b018d166cecb3f5c9869357194b872a94 
 SPL Exam Questions EN/80 - Principles of Flight.md
....@@ -38,8 +38,12 @@
3838 
3939 #### Key Terms
4040 
41
-VS = Stall Speed
42
-
41
+- **VS** = Stall Speed
42
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
43
+- **rho** — ρ (rho) — air density
44
+- **S** — Wing Area — total planform area of the wings
45
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
46
+- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
4347 ### Q3: After one wing stalls and the nose drops, what is the correct technique to prevent a spin? ^t80q3
4448 
4549 [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 @@
5963 
6064 #### Key Terms
6165 
62
-AoA = Angle of Attack
63
-
66
+- **AoA** = Angle of Attack
6467 ### Q4: Which component is responsible for pitch stabilisation during cruise? ^t80q4
6568 
6669 [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 @@
8083 
8184 #### Key Terms
8285 
83
-AoA = Angle of Attack
84
-
86
+- **AoA** = Angle of Attack
8587 ### Q5: What can happen when the never-exceed speed (VNE) is surpassed in flight? ^t80q5
8688 
8789 [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 @@
101103 
102104 #### Key Terms
103105 
104
-VNE = Never Exceed Speed
105
-
106
+- **VNE** = Never Exceed Speed
106107 ### Q6: What effect does a rearward centre of gravity position have on a glider's handling? ^t80q6
107108 
108109 [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 @@
122123 
123124 #### Key Terms
124125 
125
-CG = Centre of Gravity
126
-
126
+- **CG** = Centre of Gravity
127127 ### Q7: What purpose does the vertical tail fin (rudder assembly) serve? ^t80q7
128128 
129129 [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 @@
158158 
159159 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.
160160 
161
+#### Key Terms
162
+
163
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
164
+
161165 ### Q9: What is the relationship between aspect ratio and induced drag? ^t80q9
162166 
163167 [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 @@
174178 #### Explanation
175179 
176180 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.
181
+
182
+#### Key Terms
183
+
184
+- **D_induced** — Induced Drag — drag created as a by-product of generating lift
185
+- **AR** — Aspect Ratio — ratio of wingspan² to wing area
186
+- **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution)
187
+- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
177188 
178189 ### Q10: When the elevator trim tab is deflected downward, what is the resulting pitch tendency? ^t80q10
179190 
....@@ -209,6 +220,10 @@
209220 
210221 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.
211222 
223
+#### Key Terms
224
+
225
+- **m** — mass of the aircraft
226
+
212227 ### Q12: In straight and level flight, what happens to the required angle of attack as speed increases? ^t80q12
213228 
214229 [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 @@
228243 
229244 #### Key Terms
230245 
231
-CL = Lift Coefficient
232
-
246
+- **CL** = Lift Coefficient
247
+- **ρ** (rho) — air density
248
+- **L** — Lift — aerodynamic force acting perpendicular to the airflow
249
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
250
+- **S** — Wing Area — total planform area of the wings
233251 ### Q13: What is the function of wing fences or boundary layer fences? ^t80q13
234252 
235253 [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 @@
300318 
301319 #### Key Terms
302320 
303
-IAS = Indicated Airspeed; TAS = True Airspeed
304
-
321
+- **IAS** = Indicated Airspeed
322
+- **TAS** = True Airspeed
323
+- **ρ₀** — air density at sea level (ISA: 1.225 kg/m³)
324
+- **ρ** (rho) — air density
325
+- **q** — dynamic pressure (q = ½ × ρ × V²)
305326 ### Q17: What does the term "load factor" describe? ^t80q17
306327 
307328 [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 @@
318339 #### Explanation
319340 
320341 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).
342
+
343
+#### Key Terms
344
+
345
+- **L** — Lift — aerodynamic force acting perpendicular to the airflow
346
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
347
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
348
+- **g** — gravitational acceleration (9.81 m/s²)
321349 
322350 ### Q18: How does increasing aircraft weight affect the best glide ratio? ^t80q18
323351 
....@@ -389,8 +417,7 @@
389417 
390418 #### Key Terms
391419 
392
-CL = Lift Coefficient
393
-
420
+- **CL** = Lift Coefficient
394421 ### Q22: What is the primary function of an elevator trim tab? ^t80q22
395422 
396423 [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 @@
425452 
426453 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.
427454 
455
+#### Key Terms
456
+
457
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
458
+
428459 ### Q24: What is the centre of pressure of an aerofoil? ^t80q24
429460 
430461 [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 @@
444475 
445476 #### Key Terms
446477 
447
-AoA = Angle of Attack; CG = Centre of Gravity
448
-
478
+- **AoA** = Angle of Attack
479
+- **CG** = Centre of Gravity
449480 ### Q25: At what point during flight is parasite drag greatest? ^t80q25
450481 
451482 [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 @@
465496 
466497 #### Key Terms
467498 
468
-VNE = Never Exceed Speed
469
-
499
+- **VNE** = Never Exceed Speed
470500 ### Q26: What is the Bernoulli principle as applied to an aerofoil? ^t80q26
471501 
472502 [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 @@
520550 
521551 #### Key Terms
522552 
523
-AGL = Above Ground Level
524
-
553
+- **AGL** = Above Ground Level
525554 ### Q29: What does the term "washout" refer to in wing design? ^t80q29
526555 
527556 [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 @@
558587 
559588 #### Key Terms
560589 
561
-AoA = Angle of Attack; CL = Lift Coefficient
562
-
590
+- **AoA** = Angle of Attack
591
+- **CL** = Lift Coefficient
592
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
563593 ### Q31: How does the flap position affect the stall speed? ^t80q31
564594 
565595 [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 @@
579609 
580610 #### Key Terms
581611 
582
-VS = Stall Speed
583
-
612
+- **VS** = Stall Speed
613
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
614
+- **ρ** (rho) — air density
615
+- **S** — Wing Area — total planform area of the wings
616
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
617
+- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
584618 ### Q32: What is the purpose of a laminar-flow aerofoil? ^t80q32
585619 
586620 [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 @@
617651 
618652 #### Key Terms
619653 
620
-IAS = Indicated Airspeed; TAS = True Airspeed
621
-
654
+- **IAS** = Indicated Airspeed
655
+- **TAS** = True Airspeed
622656 ### Q34: What is the difference between static stability and dynamic stability? ^t80q34
623657 
624658 [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 @@
672706 
673707 #### Key Terms
674708 
675
-CL = Lift Coefficient
676
-
709
+- **CL** = Lift Coefficient
677710 ### Q37: In which direction does the centre of pressure move as the angle of attack increases (pre-stall)? ^t80q37
678711 
679712 [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 @@
693726 
694727 #### Key Terms
695728 
696
-AoA = Angle of Attack
697
-
729
+- **AoA** = Angle of Attack
698730 ### Q38: What determines the critical angle of attack at which a wing stalls? ^t80q38
699731 
700732 [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 @@
728760 #### Explanation
729761 
730762 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.
763
+
764
+#### Key Terms
765
+
766
+- **D_induced** — Induced Drag — drag created as a by-product of generating lift
767
+- **rho** — ρ (rho) — air density
768
+- **AR** — Aspect Ratio — ratio of wingspan² to wing area
769
+- **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution)
770
+- **S** — Wing Area — total planform area of the wings
771
+- **V** — Velocity / Airspeed
772
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
731773 
732774 ### Q40: Which types of drag make up total drag? ^t80q40
733775 
....@@ -768,8 +810,9 @@
768810 
769811 #### Key Terms
770812 
771
-AoA = Angle of Attack; CD = Drag Coefficient; CL = Lift Coefficient
772
-
813
+- **AoA** = Angle of Attack
814
+- **CD** = Drag Coefficient
815
+- **CL** = Lift Coefficient
773816 ### Q42: To recover from a stall, it is essential to ^t80q42
774817 
775818 [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 @@
789832 
790833 #### Key Terms
791834 
792
-AoA = Angle of Attack
793
-
835
+- **AoA** = Angle of Attack
794836 ### Q43: During a stall, how do lift and drag behave? ^t80q43
795837 
796838 [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 @@
810852 
811853 #### Key Terms
812854 
813
-AoA = Angle of Attack; CD = Drag Coefficient; CL = Lift Coefficient
814
-
855
+- **AoA** = Angle of Attack
856
+- **CD** = Drag Coefficient
857
+- **CL** = Lift Coefficient
858
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
815859 ### Q44: The critical angle of attack ^t80q44
816860 
817861 [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 @@
831875 
832876 #### Key Terms
833877 
834
-AoA = Angle of Attack; VS = Stall Speed
835
-
878
+- **AoA** = Angle of Attack
879
+- **VS** = Stall Speed
880
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
881
+- **rho** — ρ (rho) — air density
882
+- **S** — Wing Area — total planform area of the wings
883
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
884
+- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
836885 ### Q45: What leads to a lower stall speed Vs (IAS)? ^t80q45
837886 
838887 [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 @@
852901 
853902 #### Key Terms
854903 
855
-IAS = Indicated Airspeed; TAS = True Airspeed; VS = Stall Speed
856
-
904
+- **IAS** = Indicated Airspeed
905
+- **TAS** = True Airspeed
906
+- **VS** = Stall Speed
907
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
908
+- **rho** — ρ (rho) — air density
909
+- **W** — Weight — force due to gravity acting on the aircraft (W = m × g)
910
+- **S** — Wing Area — total planform area of the wings
911
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
912
+- **q** — dynamic pressure (q = ½ × ρ × V²)
913
+- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift
857914 ### Q46: Which statement about a spin is correct? ^t80q46
858915 
859916 [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 @@
873930 
874931 #### Key Terms
875932 
876
-AoA = Angle of Attack
877
-
933
+- **AoA** = Angle of Attack
878934 ### Q47: The laminar boundary layer on the aerofoil lies between ^t80q47
879935 
880936 [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 @@
9621018 
9631019 #### Key Terms
9641020 
965
-ISA = International Standard Atmosphere
966
-
1021
+- **ISA** = International Standard Atmosphere
9671022 ### Q52: During a sideslip, the permitted flap position is ^t80q52
9681023 
9691024 [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 @@
10341089 
10351090 #### Key Terms
10361091 
1037
-ICAO = International Civil Aviation Organization; ISA = International Standard Atmosphere
1038
-
1092
+- **ICAO** = International Civil Aviation Organization
1093
+- **ISA** = International Standard Atmosphere
10391094 ### Q56: At approximately what altitude does atmospheric pressure fall to half its sea-level value? ^t80q56
10401095 
10411096 [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 @@
10551110 
10561111 #### Key Terms
10571112 
1058
-ICAO = International Civil Aviation Organization
1059
-
1113
+- **ICAO** = International Civil Aviation Organization
10601114 ### Q57: Density altitude always corresponds to ^t80q57
10611115 
10621116 [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 @@
10761130 
10771131 #### Key Terms
10781132 
1079
-ISA = International Standard Atmosphere; QNH = Pressure adjusted to mean sea level
1080
-
1133
+- **ISA** = International Standard Atmosphere
1134
+- **QNH** = Pressure adjusted to mean sea level
10811135 ### 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
10821136 
10831137 [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 @@
10941148 #### Explanation
10951149 
10961150 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.
1151
+
1152
+#### Key Terms
1153
+
1154
+- **S** — Wing Area — total planform area of the wings
1155
+- **V** — Velocity / Airspeed
10971156 
10981157 ### Q59: The aerodynamic resultant (drag and lift) depends on air density. When air density decreases ^t80q59
10991158 
....@@ -1114,8 +1173,9 @@
11141173 
11151174 #### Key Terms
11161175 
1117
-TAS = True Airspeed
1118
-
1176
+- **TAS** = True Airspeed
1177
+- **ρ** (rho) — air density
1178
+- **q** — dynamic pressure (q = ½ × ρ × V²)
11191179 ### 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
11201180 
11211181 [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 @@
11351195 
11361196 #### Key Terms
11371197 
1138
-CG = Centre of Gravity
1139
-
1198
+- **CG** = Centre of Gravity
11401199 ### Q61: The angle between the aerofoil chord line and the aircraft's longitudinal axis is called ^t80q61
11411200 
11421201 [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 @@
12241283 
12251284 #### Key Terms
12261285 
1227
-CD = Drag Coefficient
1228
-
1286
+- **CD** = Drag Coefficient
1287
+- **ρ** (rho) — air density
1288
+- **S** — Wing Area — total planform area of the wings
1289
+- **q** — dynamic pressure (q = ½ × ρ × V²)
1290
+- **D** — Drag
12291291 ### Q66: On the speed polar, which tangent touches the curve at the point of minimum sink rate? ^t80q66
12301292 
12311293 [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 @@
12731335 
12741336 #### Key Terms
12751337 
1276
-CL = Lift Coefficient
1277
-
1338
+- **CL** = Lift Coefficient
1339
+- **D_induced** — Induced Drag — drag created as a by-product of generating lift
1340
+- **AR** — Aspect Ratio — ratio of wingspan² to wing area
1341
+- **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution)
1342
+- **S** — Wing Area — total planform area of the wings
1343
+- **q** — dynamic pressure (q = ½ × ρ × V²)
12781344 ### Q68: How does the minimum speed of an aircraft in a level turn at 45-degree bank compare to straight-and-level flight? ^t80q68
12791345 
12801346 [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 @@
12941360 
12951361 #### Key Terms
12961362 
1297
-VS = Stall Speed
1298
-
1363
+- **VS** = Stall Speed
1364
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
12991365 ### Q69: Adverse yaw is caused by ^t80q69
13001366 
13011367 [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 @@
13321398 
13331399 #### Key Terms
13341400 
1335
-CAS = Calibrated Airspeed; IAS = Indicated Airspeed; TAS = True Airspeed
1336
-
1401
+- **CAS** = Calibrated Airspeed
1402
+- **IAS** = Indicated Airspeed
1403
+- **TAS** = True Airspeed
13371404 ### Q71: The speed range authorised for the use of slotted flaps is: ^t80q71
13381405 
13391406 [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 @@
13531420 
13541421 #### Key Terms
13551422 
1356
-VA = Manoeuvring Speed
1357
-
1423
+- **VA** = Manoeuvring Speed
13581424 ### Q72: Wing tip vortices are caused by pressure equalisation from: ^t80q72
13591425 
13601426 [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 @@
14081474 
14091475 #### Key Terms
14101476 
1411
-ICAO = International Civil Aviation Organization
1412
-
1477
+- **ICAO** = International Civil Aviation Organization
14131478 ### Q75: Regarding airflow, the simplified continuity equation states: At the same moment, the same mass of air passes through different cross-sections. Therefore: ^t80q75
14141479 
14151480 [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 @@
14991564 
15001565 #### Key Terms
15011566 
1502
-ISA = International Standard Atmosphere
1503
-
1567
+- **ISA** = International Standard Atmosphere
15041568 ### Q80: The speed displayed on the airspeed indicator (ASI) is a measurement of: ^t80q80
15051569 
15061570 [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 @@
15541618 
15551619 #### Key Terms
15561620 
1557
-CL = Lift Coefficient
1558
-
1621
+- **CL** = Lift Coefficient
15591622 ### Q83: The aerodynamic centre of an aerofoil in an airflow is the point of application of: ^t80q83
15601623 
15611624 [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 @@
16091672 
16101673 #### Key Terms
16111674 
1612
-TAS = True Airspeed
1613
-
1675
+- **TAS** = True Airspeed
16141676 ### Q86: Yaw stability of an aircraft is provided by: ^t80q86
16151677 
16161678 [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 @@
16811743 
16821744 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.
16831745 
1746
+#### Key Terms
1747
+
1748
+- **ρ** (rho) — air density
1749
+
16841750 ### Q90: In the drawing below, the aerofoil chord is represented by: ^t80q90
16851751 
16861752 [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 @@
17231789 
17241790 #### Key Terms
17251791 
1726
-AoA = Angle of Attack
1727
-
1792
+- **AoA** = Angle of Attack
17281793 ### Q92: Given equal frontal area and equal airflow speed, what determines the drag of a body? ^t80q92
17291794 
17301795 [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 @@
17471812 
17481813 #### Key Terms
17491814 
1750
-CD = Drag Coefficient
1751
-
1815
+- **CD** = Drag Coefficient
1816
+- **rho** — ρ (rho) — air density
1817
+- **S** — Wing Area — total planform area of the wings
1818
+- **D** — Drag
17521819 ### Q93: What is the origin of induced drag on a wing? ^t80q93
17531820 
17541821 [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 @@
17931860 
17941861 #### Key Terms
17951862 
1796
-ICAO = International Civil Aviation Organization; ISA = International Standard Atmosphere
1797
-
1863
+- **ICAO** = International Civil Aviation Organization
1864
+- **ISA** = International Standard Atmosphere
17981865 ### Q95: In the aerofoil diagram below, which line represents the mean camber line? ^t80q95
17991866 
18001867 [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 @@
18601927 
18611928 #### Key Terms
18621929 
1863
-AoA = Angle of Attack; VNE = Never Exceed Speed
1864
-
1930
+- **AoA** = Angle of Attack
1931
+- **VNE** = Never Exceed Speed
18651932 ### Q98: At what condition does airflow separation from an aerofoil occur? ^t80q98
18661933 
18671934 [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 @@
18851952 
18861953 #### Key Terms
18871954 
1888
-AoA = Angle of Attack
1889
-
1955
+- **AoA** = Angle of Attack
18901956 ### Q99: What is the mean gravitational acceleration at the surface of the Earth? ^t80q99
18911957 
18921958 [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 @@
19101976 
19111977 #### Key Terms
19121978 
1913
-ISA = International Standard Atmosphere
1914
-
1979
+- **ISA** = International Standard Atmosphere
19151980 ### Q100: True Airspeed (TAS) is obtained from the airspeed indicator (ASI) reading by: ^t80q100
19161981 
19171982 [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 @@
19352000 
19362001 #### Key Terms
19372002 
1938
-CAS = Calibrated Airspeed; IAS = Indicated Airspeed; ISA = International Standard Atmosphere; TAS = True Airspeed
1939
-
2003
+- **CAS** = Calibrated Airspeed
2004
+- **IAS** = Indicated Airspeed
2005
+- **ISA** = International Standard Atmosphere
2006
+- **TAS** = True Airspeed
19402007 ### Q101: A shift of the centre of gravity is caused by: ^t80q101
19412008 
19422009 [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 @@
19602027 
19612028 #### Key Terms
19622029 
1963
-CG = Centre of Gravity
1964
-
2030
+- **CG** = Centre of Gravity
19652031 ### Q102: The high-lift device shown in the diagram is a: ^t80q102
19662032 
19672033 [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 @@
20282094 
20292095 #### Key Terms
20302096 
2031
-ICAO = International Civil Aviation Organization
2032
-
2097
+- **ICAO** = International Civil Aviation Organization
20332098 ### Q105: The airspeed indicator (ASI) reading is based on a measurement of: ^t80q105
20342099 
20352100 [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 @@
20502115 - **Option A** is nonsensical — a weathervane measures wind direction, not pressure.
20512116 - **Option C** is wrong because measuring only total pressure without subtracting static pressure gives no speed information.
20522117 - **Option D** is also incorrect because static pressure alone tells you only about altitude, not airspeed.
2118
+
2119
+#### Key Terms
2120
+
2121
+- **rho** — ρ (rho) — air density
2122
+- **q** — dynamic pressure (q = ½ × ρ × V²)
2123
+- **D** — Drag
20532124 
20542125 ### Q106: Roll stability is influenced by: ^t80q106
20552126 
....@@ -2095,8 +2166,8 @@
20952166 
20962167 #### Key Terms
20972168 
2098
-VA = Manoeuvring Speed; VNE = Never Exceed Speed
2099
-
2169
+- **VA** = Manoeuvring Speed
2170
+- **VNE** = Never Exceed Speed
21002171 ### Q108: When the wing's angle of incidence is larger at the root than at the tip, this is called: ^t80q108
21012172 
21022173 [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 @@
21172188 - **Option A** (aspect ratio) is the span-to-chord ratio.
21182189 - **Option B** (aerodynamic twist) achieves a similar stall progression by using different aerofoil profiles along the span rather than physical twist.
21192190 - **Option D** (interference compensation) is not a standard aerodynamic term for wing twist.
2191
+
2192
+#### Key Terms
2193
+
2194
+- **D** — Drag
21202195 
21212196 ### Q109: Barometric pressure in the Earth's atmosphere has the characteristic of: ^t80q109
21222197 
....@@ -2335,8 +2410,7 @@
23352410 
23362411 #### Key Terms
23372412 
2338
-CG = Centre of Gravity
2339
-
2413
+- **CG** = Centre of Gravity
23402414 ### Q119: What benefit does differential aileron deflection provide? ^t80q119
23412415 
23422416 [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 @@
24442518 
24452519 #### Key Terms
24462520 
2447
-CL = Lift Coefficient
2448
-
2521
+- **CL** = Lift Coefficient
2522
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
24492523 ### Q124: In a coordinated turn, what is the relationship between load factor (n) and stall speed (Vs)? ^t80q124
24502524 
24512525 [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 @@
24682542 
24692543 #### Key Terms
24702544 
2471
-VS = Stall Speed
2472
-
2545
+- **VS** = Stall Speed
2546
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
2547
+- **D** — Drag
24732548 ### Q125: The pressure equalisation between the upper and lower wing surfaces results in ^t80q125
24742549 
24752550 [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 @@
25342609 
25352610 #### Key Terms
25362611 
2537
-CD = Drag Coefficient; CL = Lift Coefficient
2538
-
2612
+- **CD** = Drag Coefficient
2613
+- **CL** = Lift Coefficient
25392614 ### Q128: Any arbitrarily shaped body placed in an airflow (v > 0) always produces ^t80q128
25402615 
25412616 [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 @@
26472722 
26482723 #### Key Terms
26492724 
2650
-CL = Lift Coefficient
2651
-
2725
+- **CL** = Lift Coefficient
2726
+- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling
26522727 ### Q133: What is the aerodynamic effect of deploying airbrakes? ^t80q133
26532728 
26542729 [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 @@
26932768 
26942769 #### Key Terms
26952770 
2696
-CG = Centre of Gravity
2697
-
2771
+- **CG** = Centre of Gravity
26982772 ### Q135: What distinguishes a spin from a spiral dive? ^t80q135
26992773 
27002774 [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 @@
27382812 
27392813 #### Key Terms
27402814 
2741
-CG = Centre of Gravity
2742
-
2815
+- **CG** = Centre of Gravity
27432816 ### Q137: Which structural element provides directional stability? ^t80q137
27442817 
27452818 [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 @@
27852858 
27862859 #### Key Terms
27872860 
2788
-AoA = Angle of Attack
2789
-
2861
+- **AoA** = Angle of Attack
27902862 ### Q139: What is one function of the horizontal tail? ^t80q139
27912863 
27922864 [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 @@
28512923 
28522924 #### Key Terms
28532925 
2854
-AoA = Angle of Attack
2855
-
2926
+- **AoA** = Angle of Attack
28562927 ### Q142: How is the force balance affected during a banked turn? ^t80q142
28572928 
28582929 [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 @@
28732944 - **Option A** is wrong because more, not less, lift is needed.
28742945 - **Option B** is imprecise — from the aircraft's reference frame it appears as centrifugal force, but the actual physics involves centripetal force.
28752946 - **Option D** does not fully describe the force balance requirement.
2947
+
2948
+#### Key Terms
2949
+
2950
+- **n** — Load Factor (ratio of lift to weight: n = L/W)
2951
+- **D** — Drag
28762952 
28772953 ### Q143: On a Touring Motor Glider (TMG), which engine arrangement produces the least drag? ^t80q143
28782954 
....@@ -2895,8 +2971,7 @@
28952971 
28962972 #### Key Terms
28972973 
2898
-TMG = Touring Motor Glider
2899
-
2974
+- **TMG** = Touring Motor Glider
29002975 ### Q144: What effect is known as "adverse yaw"? ^t80q144
29012976 
29022977 [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 @@
29853060 
29863061 #### Key Terms
29873062 
2988
-CG = Centre of Gravity
2989
-
3063
+- **CG** = Centre of Gravity
29903064 ### 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
29913065 
29923066 [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 @@
30283102 - **Option A** is not universally correct — winch launch flap settings vary by type.
30293103 - **Option B** reverses the restriction.
30303104 - **Option D** is wrong because negative camber is a cruise setting, not appropriate for the high-lift-demand winch launch phase.
3105
+
3106
+#### Key Terms
3107
+
3108
+- **D** — Drag
30313109 
30323110 ### Q150: On the aerofoil diagram, what does point number 3 represent? ^t80q150
30333111 
....@@ -3140,8 +3218,7 @@
31403218 
31413219 #### Key Terms
31423220 
3143
-CG = Centre of Gravity
3144
-
3221
+- **CG** = Centre of Gravity
31453222 ### Q155: Which description characterises static stability? ^t80q155
31463223 
31473224 [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 @@
32263303 - **Option C** is incorrect because drag increases with V² — it is not constant.
32273304 - **Option D** is physically impossible — drag-free flight does not exist in a real fluid.
32283305 
3306
+#### Key Terms
3307
+
3308
+- **D** — Drag
3309
+
32293310 ### Q159: "Longitudinal stability" refers to stability around which axis? ^t80q159
32303311 
32313312 [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 @@
32683349 - **Option C** (drag per weight) describes a drag-to-weight ratio.
32693350 - **Option D** (wing area per weight) is the mathematical inverse of wing loading.
32703351 
3352
+#### Key Terms
3353
+
3354
+- **D** — Drag
3355
+
32713356 ### Q161: What phenomenon is known as adverse yaw? ^t80q161
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32733358 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q161) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q161)