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Exam simulation Principles of Flight ATPL - Airline Transport Pilot license

Exam simulation ATPL Principles of Flight 120 questions on 120 minutes

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1 - A commercial jet aeroplane is performing a straight descent at a constant Mach number with constant mass. The operational speed limit that may be exceeded is:
2 - Vortex generators on the upper side of the wing surface will:
3 - Which statement about induced drag and tip vortices is correct?
4 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
5 - An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:
6 - Increasing dynamic pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant):
7 - In straight and level flight, as speed is increased:
8 - How are the speeds (shown in the figure) at point 1 and point 2 related to the relative wind / airflow V?
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9 - Extension of FOWLER type trailing edge lift augmentation devices, will produce:
10 - The stall speed (IAS) will change according to the following factors:
11 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
12 - Which of the following statements is true?
13 - What can happen to the aeroplane structure flying at a speed just exceeding VA ?
14 - When are outboard ailerons (if present) de-activated?
15 - Compared with the clean configuration, the angle of attack at CLmax with trailing edge flaps extended is:
16 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
17 - Does the pitch angle of a constant speed propeller alter in medium horizontal turbulence?
18 - The angle of attack for a propeller blade is the angle between the blade chord line and the:
19 - To be able to predict compressibility effects you have to determine the:
20 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
21 - Upon extension of a spoiler on a wing:
22 - Increase of wing loading will:
23 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. An increase in angle of attack of 1 degree will increase CL by 0.09. A vertical up gust instantly changes the angle of attack by 5 degrees. The load factor will be:
24 - Which of the following aeroplane parts affect induced drag most?
25 - Which line represents the total drag line of an aeroplane?
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26 - Which statement is correct about the laminar and turbulent boundary layer:
27 - The following factors increase stall speed:
28 - A jet aeroplane equipped with inboard and outboard ailerons is cruising at its normal cruise Mach number. In this case
29 - The angle of attack of a wing profile is defined as the angle between:
30 - Which statement with respect to the speed of sound is correct ?
31 - In case the Mach trimmer fails:
32 - During an erect spin recovery:
33 - Given the following aeroplane configurations:1. Clean wing2. Slats only extended3. Flaps only extendedPlace these configurations in order of stall angle of attack:
34 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls ?
35 - Tick force per g is independent of altitude.II Stick force per g increases when the centre of gravity moves forward.
36 - Which type of flap is shown in the picture?
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37 - An aeroplane has a stall speed of 100 KT at a load factor n = 1. In a turn with a load factor of n = 2, the stall speed is:
38 - Which aeroplane behaviour will be corrected by a yaw damper ?
39 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
40 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
41 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
42 - Which statement is correct regarding a shockwave on a lift generating wing?
43 - When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of:
44 - If in a two-dimensional incompressible and subsonic flow, the streamlines converge the static pressure in the flow will:
45 - Which of the following situations leads to a decreasing stall speed (IAS)?
46 - The lift- and drag forces, acting on a wing cross section:
47 - The boundary layer of a wing is:
48 - In what flight phase are the outboard ailerons (if present) not operated ?
49 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
50 - Bernoulli's equation can be written as:(pt= total pressure, ps = static pressure and q=dynamic pressure)
51 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position ?
52 - With increasing altitude and constant IAS the static lateral stability ( 1) and the dynamic lateral/directional stability ( 2) of an aeroplane with swept-back wing will:
53 - An aeroplane has a stall speed of 78 KCAS at its gross weight of 6850 lbs. What is the stall speed when the weight is 5000 lbs?
54 - The maximum aft position of the centre of gravity is, amongst others, limited by the:
55 - Ground effect has the following influence on the landing distance:
56 - The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from:
57 - The manoeuvrability of an aeroplane is best when the:
58 - Which statement is correct in respect of CL and angle of attack?
59 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is:
60 - Which statement is correct?I. Stall speeds are determined with the CG at the aft limit.II. Minimum control speeds are determined with the CG at the forward limit.
61 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim?
62 - The Mach number:
63 - Assuming ISA conditions, climbing at a constant Mach Number up to FL 350 the TAS will:
64 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
65 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
66 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
67 - In a convergent tube with an incompressible sub-sonic airflow, the following pressure changes will occur:Ps = static pressure.Pdyn = dynamic pressure. Ptot = total pressure.
68 - Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
69 - Induced drag at constant IAS is affected by:
70 - How does stalling speed (IAS) vary with altitude?
71 - The SI units of air density (I) and force (II) are:
72 - Given an initial condition in straight and level flight with a speed of 1.4 VS. The maximum bank angle attainable without stalling in a steady co-ordinated turn, whilst maintaining speed and altitude, is approximately:
73 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
74 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
75 - A laminar boundary layer is a layer, in which:
76 - When the air has passed through a normal shock wave the Mach number is
77 - Gyroscopic precession of a propeller is induced by:
78 - The bow wave will first appear at:
79 - Which statement about a primary control surface controlled by a servo tab, is correct?
80 - An aeroplane is in a level turn, at a constant TAS of 300 kt, and a bank angle of 45°. Its turning radius is:(given: g= 10 m/s 2)
81 - When flaps are extended in a straight and level flight at constant IAS, the lift coefficient will eventually:
82 - Vortex generators:
83 - The bank angle in a rate-one turn depends on:
84 - What is the effect of an aft shift of the centre of gravity on ( 1) static longitudinal stability and( 2) the required control deflection for a given pitch change?
85 - In a steady level, co-ordinated turn, the load factor n and the stalling speed VS will be:
86 - Load factor is:
87 - The speed of sound is affected by the:
88 - Deploying a Fowler flap, the flap will:
89 - 'Flutter' may be caused by:
90 - When a strongly swept back wing stalls and the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be a(n):
91 - What factors determine the distance travelled over the ground of an aeroplane in a glide ?
92 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes:
93 - VLE is defined as the:
94 - The manoeuvre stability of a large jet transport aeroplane is 280 N / g. What stick force is required, if the aeroplane is pulled to the limit manoeuvring load factor from a trimmed horizontal straight and steady flight? (cruise configuration)
95 - What is the limit load factor of a large transport aeroplane?
96 - Assuming ISA conditions, which statement with respect to the climb is correct ?
97 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
98 - If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move:
99 - Consider an aeroplane with: 1 a trim tab.2 fully powered hydraulic controls and an adjustable horizontal stabiliser.For both cases and starting from a trimmed condition, how will the neutral position of the control column change, after trimming for a speed increase?
100 - The true airspeed (TAS) is:
101 - Which one of the following statements about Bernoulli's theorem is correct?
102 - Mach buffet occurs:
103 - Assuming no compressibility effects, induced drag at constant IAS is affected by:
104 - If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes? (low speed, subsonic and incompressible flow)
105 - Which of the following ( 1) aerofoils and ( 2) angles of attack will produce the lowest Mcrit values?
106 - The function of the stick pusher is:
107 - Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
108 - When 'spoilers' are used as speed brakes:
109 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
110 - The relative thickness of an aerofoil is expressed as:
111 - Static lateral stability should not be too small, because:
112 - What is the SI unit of measurement for power?
113 - Increasing the number of propeller blades will:
114 - The 'short period mode' is an:
115 - VA is:
116 - Which of the following statements about stall speed is correct?
117 - Trailing edge flap extension will:
118 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
119 - The stall speed:
120 - How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight?
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