From c7fe4faf1aab7bd121763380c10be86d95a80333 Mon Sep 17 00:00:00 2001 From: Matthias Nott <mnott@mnsoft.org> Date: Sun, 22 Mar 2026 17:21:58 +0100 Subject: [PATCH] fix: Q71 answer correction, Q39 wording, remove bogus Oswald terms --- SPL Exam Questions EN/80 - Principles of Flight.md | 132 ++++++++++++++++++------------------------- 1 files changed, 56 insertions(+), 76 deletions(-) diff --git a/SPL Exam Questions EN/80 - Principles of Flight.md b/SPL Exam Questions EN/80 - Principles of Flight.md index bab7a12..11342f0 100644 --- a/SPL Exam Questions EN/80 - Principles of Flight.md +++ b/SPL Exam Questions EN/80 - Principles of Flight.md @@ -38,11 +38,11 @@ #### Key Terms -- **VS** = Stall Speed -- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) - **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_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **VS** = Stall Speed - **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 @@ -160,9 +160,7 @@ #### Key Terms -- **n** — Load Factor (ratio of lift to weight: n = L/W) 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) @@ -186,7 +184,6 @@ - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift - **AR** — Aspect Ratio — ratio of wingspan² to wing area - **e** — Oswald Efficiency Factor — wing efficiency factor (1.0 for ideal elliptical lift distribution) - ### Q10: When the elevator trim tab is deflected downward, what is the resulting pitch tendency? ^t80q10 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q10) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q10) @@ -223,9 +220,7 @@ #### Key Terms -- **m** — mass of the aircraft 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) @@ -245,10 +240,10 @@ #### Key Terms -- **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) +- **CL** = Lift Coefficient +- **ρ** (rho) — air density - **S** — Wing Area — total planform area of the wings ### Q13: What is the function of wing fences or boundary layer fences? ^t80q13 @@ -321,10 +316,10 @@ #### Key Terms - **IAS** = Indicated Airspeed +- **q** — dynamic pressure (q = ½ × ρ × V²) +- **ρ** (rho) — air density - **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) @@ -344,11 +339,10 @@ #### 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) +- **L** — Lift — aerodynamic force acting perpendicular to the airflow - **g** — gravitational acceleration (9.81 m/s²) - +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) ### Q18: How does increasing aircraft weight affect the best glide ratio? ^t80q18 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q18) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q18) @@ -419,8 +413,7 @@ #### Key Terms -- **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift -CL = Lift Coefficient +CL — Lift Coefficient — dimensionless measure of aerodynamic lift ### 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) @@ -457,7 +450,6 @@ #### Key Terms -- **n** — Load Factor (ratio of lift to weight: n = L/W) n — Load Factor (ratio of lift to weight: n = L/W) ### Q24: What is the centre of pressure of an aerofoil? ^t80q24 @@ -500,8 +492,7 @@ #### Key Terms -- **VNE** — Never Exceed Speed -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) @@ -592,8 +583,8 @@ #### Key Terms -- **AoA** = Angle of Attack - **CL** = Lift Coefficient +- **AoA** = Angle of Attack - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling ### Q31: How does the flap position affect the stall speed? ^t80q31 @@ -614,11 +605,11 @@ #### Key Terms -- **VS** = Stall Speed -- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) - **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_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **VS** = Stall Speed - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q32: What is the purpose of a laminar-flow aerofoil? ^t80q32 @@ -656,8 +647,8 @@ #### Key Terms -- **IAS** = Indicated Airspeed - **TAS** = True Airspeed +- **IAS** = Indicated 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) @@ -764,18 +755,17 @@ #### 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. +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 options B and 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 +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) - **rho** — ρ (rho) — air density +- **V** — Velocity / Airspeed +- **S** — Wing Area — total planform area of the wings - **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 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q40) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q40) @@ -816,8 +806,8 @@ #### Key Terms - **AoA** = Angle of Attack -- **CD** = Drag Coefficient - **CL** = Lift Coefficient +- **CD** = Drag 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) @@ -857,10 +847,10 @@ #### Key Terms -- **AoA** = Angle of Attack -- **CD** = Drag Coefficient - **CL** = Lift Coefficient +- **AoA** = Angle of Attack - **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **CD** = Drag Coefficient ### 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) @@ -880,12 +870,12 @@ #### Key Terms -- **AoA** = Angle of Attack -- **VS** = Stall Speed -- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) - **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_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **AoA** = Angle of Attack +- **VS** = Stall Speed - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q45: What leads to a lower stall speed Vs (IAS)? ^t80q45 @@ -906,15 +896,15 @@ #### Key Terms -- **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) +- **TAS** = True Airspeed +- **IAS** = Indicated Airspeed - **q** — dynamic pressure (q = ½ × ρ × V²) +- **rho** — ρ (rho) — air density +- **S** — Wing Area — total planform area of the wings +- **CL_max** — Maximum Lift Coefficient — highest CL the wing can produce before stalling +- **n** — Load Factor (ratio of lift to weight: n = L/W) +- **VS** = Stall Speed - **CL** — Lift Coefficient — dimensionless measure of aerodynamic lift ### Q46: Which statement about a spin is correct? ^t80q46 @@ -1023,7 +1013,8 @@ #### Key Terms -ISA = International Standard Atmosphere +- **ISA** = International Standard Atmosphere +- **W** — Weight — force due to gravity acting on the aircraft (W = m × g) ### 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) @@ -1094,8 +1085,8 @@ #### Key Terms -- **ICAO** = International Civil Aviation Organization - **ISA** = International Standard Atmosphere +- **ICAO** = International Civil Aviation Organization ### 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) @@ -1178,9 +1169,9 @@ #### Key Terms -- **TAS** = True Airspeed -- **ρ** (rho) — air density - **q** — dynamic pressure (q = ½ × ρ × V²) +- **ρ** (rho) — air density +- **TAS** = True Airspeed ### 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) @@ -1200,8 +1191,7 @@ #### Key Terms -- **CG** — Centre of Gravity -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) @@ -1289,11 +1279,11 @@ #### Key Terms -- **CD** = Drag Coefficient -- **ρ** (rho) — air density - **S** — Wing Area — total planform area of the wings - **q** — dynamic pressure (q = ½ × ρ × V²) +- **ρ** (rho) — air density - **D** — Drag +- **CD** = Drag Coefficient ### 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) @@ -1341,12 +1331,12 @@ #### Key Terms -- **CL** = Lift Coefficient - **D_induced** — Induced Drag — drag created as a by-product of generating lift +- **CL** = Lift Coefficient - **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) +- **S** — Wing Area — total planform area of the wings ### 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) @@ -1366,8 +1356,8 @@ #### Key Terms -- **VS** = Stall Speed - **n** — Load Factor (ratio of lift to weight: n = L/W) +- **VS** = Stall Speed ### 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) @@ -1404,9 +1394,9 @@ #### Key Terms -- **CAS** = Calibrated Airspeed -- **IAS** = Indicated Airspeed - **TAS** = True Airspeed +- **IAS** = Indicated Airspeed +- **CAS** = Calibrated 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) @@ -1819,10 +1809,10 @@ #### Key Terms +- **D** — Drag - **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) @@ -1867,8 +1857,8 @@ #### Key Terms -- **ICAO** = International Civil Aviation Organization - **ISA** = International Standard Atmosphere +- **ICAO** = International Civil Aviation Organization ### 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) @@ -1934,8 +1924,8 @@ #### Key Terms -- **AoA** = Angle of Attack - **VNE** = Never Exceed Speed +- **AoA** = Angle of Attack ### 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) @@ -2007,10 +1997,10 @@ #### Key Terms -- **CAS** = Calibrated Airspeed -- **IAS** = Indicated Airspeed -- **ISA** = International Standard Atmosphere - **TAS** = True Airspeed +- **IAS** = Indicated Airspeed +- **CAS** = Calibrated Airspeed +- **ISA** = International Standard Atmosphere ### 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) @@ -2125,10 +2115,9 @@ #### Key Terms -- **rho** — ρ (rho) — air density - **q** — dynamic pressure (q = ½ × ρ × V²) +- **rho** — ρ (rho) — air density - **D** — Drag - ### Q106: Roll stability is influenced by: ^t80q106 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q106) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q106) @@ -2198,9 +2187,7 @@ #### Key Terms -- **D** — Drag D — Drag - ### Q109: Barometric pressure in the Earth's atmosphere has the characteristic of: ^t80q109 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q109) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q109) @@ -2550,9 +2537,9 @@ #### Key Terms -- **VS** = Stall Speed - **n** — Load Factor (ratio of lift to weight: n = L/W) - **D** — Drag +- **VS** = Stall Speed ### 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) @@ -2617,8 +2604,8 @@ #### Key Terms -- **CD** = Drag Coefficient - **CL** = Lift Coefficient +- **CD** = Drag 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) @@ -2957,7 +2944,6 @@ - **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 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q143) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q143) @@ -3113,9 +3099,7 @@ #### Key Terms -- **D** — Drag D — Drag - ### Q150: On the aerofoil diagram, what does point number 3 represent? ^t80q150 [DE](../SPL%20Exam%20Questions%20DE/80%20-%20Grundlagen%20des%20Fliegens.md#^t80q150) · [FR](../SPL%20Exam%20Questions%20FR/80%20-%20Principes%20du%20vol.md#^t80q150) @@ -3314,9 +3298,7 @@ #### Key Terms -- **D** — Drag 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) @@ -3361,9 +3343,7 @@ #### Key Terms -- **D** — Drag 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