- Study guides, Class notes & Summaries

When Climbing at a constant Mach number the Calibrated Airspeed (C.A.S.) will: - correct answer Decrease When climbing at a constant Mach number the True Airspeed (TAS) will? - correct answer Decrease if the temperature decreases. The difference between leading edge slats and leading edge flaps is? - correct answer Slats reenergise the boundary layering. Flaps alter the effective camber...

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4 pages

Written in 2024/2025

Grade A+

RealGrades

What can you do with an ATPL aside from PPL/CPL privledges? - correct answer Be the PIC of an aircraft that requires a co-pilot on ATO for hire or reward What is the weight that the aircrafthas to be above before an ATPL is required? - correct answer 5700kg, but now only states 2 crew.. Is your ATPL/Instrument ratings current outside of Air NSN? - correct answer Yes the ATPL is, but not...

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7 pages

Written in 2024/2025

Grade A+

RealGrades

List what you need to do for a pallet/how boxes can fit in a/c question? - correct answer 1. Find floor loading max limit 2. Find Running Load max limit 3. Get compartment max weight limit from W & B booklet 4. Use the lowest of the 3 values 5. Subtract the pallet itself weight. 6. Divide remaining value into single box weight to find how many boxes will fit on pallet How do you find the floor loading max limit? - correct answer ...

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13 pages

Written in 2024/2025

Grade A+

RealGrades

The angle between the aeroplane longitude axis and the chord line is the: - correct answer Angle of incidence The point about which the pitching moment is independent of angle of attack is called: - correct answer The aerodynamic centre The unit of the density of the air and the force are: - correct answer kg/m3 and N In recovery from a spin : - correct answer ...

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4 pages

Written in 2024/2025

Grade A+

RealGrades

Vmca - correct answer minimum control speed, air atleast 1.2 Vs V1 - correct answer Decision speed. Lower limit is Vmcg plus recognition time. upper limit Vmbe or Vr Vr - correct answer Rotation speed. Not less than V1 1.05 Vmca V2 - correct answer Initial climb speed. Lowet limits are 1.2 Vs or 1.1 Vmca 1st segment climb gradient - correct an...

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2 pages

Written in 2024/2025

Grade A+

RealGrades

The lift equation - correct answer L = ½×ρ×V²×S×Cι ρ = air density V = TAS S = surface area of wings Cl = lift coefficient, determined by the shape and AOA of the wing What are the 3 types of parasitic drag? - correct answer Skin friction Form drag Interference drag The speed of sound equation - correct answer Speed of sound (kts) = 39×√Temp (K) How to convert...

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3 pages

Written in 2024/2025

Grade A+

RealGrades

Total pressure - correct answer Dynamic pressure + static pressure Dynamic pressure formula - correct answer ½ρv² Taper ratio - correct answer tip chord and root chord Aspect ratio - correct answer wing span squared and wing area Fineness ratio - correct answer chord and thickness Wing sweep - correct answ...

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4 pages

Written in 2024/2025

Grade A+

RealGrades

Atmosphere pressure decrease per 1000ft at 1) lower levels 2) higher levels - correct answer 1) 27hPa 2) 50hPa CAS is ___ corrected for ___ - correct answer IAS, position and instrument EAS is ___ corrected for ___ - correct answer CAS, compressibility TAS is ___ corrected for ___ - correct answer EAS, density LSS formula - correct answer ...

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2 pages

Written in 2024/2025

Grade A+

RealGrades

Wing loading - correct answer Is the loading weight of the aircraft/ the area of the wing Higher wing loading higher load factor Supercritical aerofoil: - correct answer A large nose radius, flatter upper surface and a negative as well as positive camber Propeller efficiency: - correct answer Power out ( Thrust x TAS) / Power inn ( Engine Torque x RPM -shaft power) Sideslip angle ...

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2 pages

Written in 2024/2025

Grade A+

RealGrades

aerodynamic loads felt by the skin - correct answer transferred to larger structural components structural components include - correct answer wing spars, longerons, stringers, frames, bulkheads etc aerodynamic loads - correct answer safely absorbed by skin and structural components if you exceed design limits - correct answer permanent damage to st...

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12 pages

Written in 2024/2025

Grade A+

RealGrades

1. Regarding a positively cambered aerofoil section, which statement is correct? 1) The angle of attack has a negative value when the lift coefficient equals zero. 2) A nose up pitching moment exists when the lift coefficient equals zero. A. 1) incorrect, 2) incorrect. B. 1) correct, 2) correct. C. 1) incorrect, 2) correct. D. 1) correct, 2) incorrect. - correct answer D When a turn is initiated, adverse yaw is: A. the tendency of an aeroplane to yaw in...

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60 pages

Written in 2024/2025

Grade A+

RealGrades

Which of these statements about a steady subsonic flow are correct or incorrect? 1. The static pressure increases as the streamlines diverge. 2. The velocity decreases as the streamlines diverge. - correct answer Both correct With an increase in section area flow speed decreases as there is more room to space out the airflow, dynamic pressure decreases as streamlines dverge. Which statement, about an aeroplane entering ground effect at constant angle...

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7 pages

Written in 2024/2025

Grade A+

RealGrades

1. To maintain altitude, what must be done as Indicated Airspeed (IAS) is reduced? - correct answer b. Increase angle of attack to maintain the correct lift force. 2. If more lift force is required because of greater operating weight, what must be done to fly at the angle of attack which corresponds to CLMAX? - correct answer d. Increase the Indicated Airspeed (IAS). 3. Which of the following statements is correct? 1. T...

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5 pages

Written in 2024/2025

Grade A+

RealGrades

POF Questions with Complete Correct Answers | Grade A+

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9 items

Passit

What is the formula of Lift? Ans: L=Cl*1/2Rho*V^2*S Cl: Coefficient of Lift - Rho : Density - V: Velocity - S: Surface area of the wing What is the formula of Drag? Ans: D=Cd*1/2Rho*V^2*S Cd: Coefficient of Drag - Rho : Density - V: Velocity - S: Surface area of the wing What is the formula to find the CDI (coefficient of induced drag)? Ans: CDI=Cl^2/Aspect ratio What is the formula of the load factor in a turn? Ans: LF=1/Cos Gamma (gamma is the angle of bank) What is the formula to fi...

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5 pages

Written in 2023/2024

Grade A+

Passit