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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 - Washout is:
2 - 'Tuck under' may happen at:
3 - 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:
4 - Which has the effect of increasing load factor? (all other relevant factors being constant)
5 - Which of the following statements about boundary layers is correct?
6 - The correct drag formula is:
7 - The continuity equation states: If the area of a tube is increasing, the speed of the subsonic and incompressible flow inside is
8 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
9 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls?
10 - How is stall warning presented to the pilots of a large transport aeroplane?
11 - An aeroplane has the following flap settings: 0°, 15°, 30° and 45°. Slats can also be selected. Which of the following selections will most adversely affect the CL / CD ratio?
12 - If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move:
13 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
14 - A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:
15 - 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?
16 - In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is
17 - The stall speed:
18 - Induced drag may be reduced by:
19 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
20 - The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of:
21 - Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
22 - During an erect spin recovery:
23 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
24 - A jet aeroplane is cruising at high altitude with a Mach-number, that provides a buffet margin of 0.3g incremental. In order to increase the buffet margin to 0.4g incremental the pilot must:
25 - The effect of the wing downwash on the static longitudinal stability of an aeroplane is:
26 - Consider the steady flow through a stream tube where the velocity of the stream is V. An increase in temperature of the flow at a constant value of V will:
27 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
28 - What wing shape or wing characteristic is the least sensitive to turbulence:
29 - How does stalling speed (IAS) vary with altitude?
30 - A CG location beyond the aft limit leads to:
31 - A slotted flap will increase the CLmax by:
32 - The unit of measurement of pressure is:
33 - A conventional stabiliser on a stable aeroplane in a normal cruise condition: 1 - always provides negative lift. 2 - contributes to the total lift of the aeroplane. 3 - may stall before the wing, in icing conditions, with large flap settings, unless adequate design and/or operational precautions are taken. 4 - is necessary to balance the total pitch moment of the aeroplane. Which of the following lists all the correct statements?
34 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
35 - In the transonic range the aeroplane characteristics are strongly determined by:
36 - After the transition point between the laminar and turbulent boundary layer
37 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is:
38 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
39 - What is the influence of decreasing aeroplane weight on Mcrit at constant IAS?
40 - VLE is defined as the:
41 - The 'short period mode' is an:
42 - Which statement is correct at the speed for minimum drag (subsonic)?
43 - During the take-off roll with a strong crosswind from the left, a four engine jet aeroplane with wing mounted engines experiences an engine failure above V1. Which engine causes the greatest control problem?
44 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
45 - Air passes a normal shock wave. Which of the following statements is correct?
46 - Given two identical aeroplanes with wing mounted engines, one fitted with jet engines and the other with counter rotating propellers, what happens following an engine failure?
47 - Which statement about stick force per g is correct?
48 - Compared with the clean configuration, the angle of attack at CLmax with trailing edge flaps extended is:
49 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
50 - Extension of FOWLER type trailing edge lift augmentation devices, will produce:
51 - In general transport aeroplanes with power assisted flight controls are fitted with an adjustable stabilizer instead of trim tabs on the elevator. This is because:
52 - For a positive cambered aerofoil, the CL-alpha curve intersects the vertical CL axis:
53 - When 'spoilers' are used as speed brakes:
54 - The stall speed increases, when: (all other factors of importance being constant)
55 - Upon extension of a spoiler on a wing:
56 - One important advantage the turbulent boundary layer has over the laminar layer is that:
57 - 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)
58 - The stalling speed in IAS will change according to the following factors:
59 - Spoiler deflection causes:
60 - The effect of a positive wing sweep on static directional stability is as follows:
61 - The speed of sound is affected by the:
62 - Total pressure is: (rho = density)
63 - The formula for the Mach Number is: (a= speed of sound)
64 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim?
65 - What is the advantage of a variable incidence tailplane over a fixed incidence tailplane with elevator and trim tab?
66 - What increases the stalling angle of attack? Use of:
67 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
68 - 'Flutter' may be caused by:
69 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
70 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
71 - Which statement is correct about a spring tab?
72 - The lift formula is: (rho = density)
73 - Which of the following flight phenomena can occur at Mach numbers below the critical Mach number?
74 - Which statement is correct? The lift to drag ratio determines the
75 - When the air is passing through a shock wave the static temperature will
76 - Which statement about a jet transport aeroplane is correct during take-off with the cg at the forward limit and the trimmable horizontal stabiliser (THS) positioned at the maximum allowable aeroplane nose down position?
77 - Two identical aircraft A and B, with the same mass, are flying steady level co-ordinated 20 degree bank turns. If the TAS of A is 130 KT and that of B is 200 KT:
78 - Critical Mach number is the free stream Mach number at which:
79 - Assuming ISA conditions, climbing at a constant Mach Number up to FL 350 the TAS will:
80 - If an aeroplane flies in the ground effect
81 - 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:
82 - The high lift device shown in the figure is a:
question pof4.webp
83 - To increase the critical Mach number a conventional aerofoil should
84 - The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with:
85 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position?
86 - The high lift device shown in the figure below is a:
question pof5.webp
87 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:
88 - Which of the following will reduce induced drag?
89 - 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.
90 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
91 - Gyroscopic precession of a propeller is induced by:
92 - The pitching moment versus angle of attack line in the diagram, which corresponds to a CG located at the neutral point of a given aeroplane at low and moderate angles of attack is:
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93 - In straight and level flight, as speed is reduced:
94 - The Mach number:
95 - How does positive camber of an aerofoil affect static longitudinal stability?
96 - The effect of a ventral fin on the static stability of an aeroplane is as follows: (1=longitudinal, 2=lateral, 3=directional)
97 - The frontal area of a body, placed in a certain airstream is increased by a factor 3. The shape will not alter. The aerodynamic drag will increase with a factor:
98 - The induced angle of attack is the result of:
99 - Which type of flap is shown in the picture?
question pof1.webp
100 - Assuming no compressibility effects, induced drag at constant IAS is affected by:
101 - 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:
102 - The angle between the airflow (relative wind) and the chord line of an aerofoil is:
103 - The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are:
104 - Mach buffet occurs:
105 - Dangerous stall characteristics, in large transport aeroplanes that require stick pushers to be installed, include:
106 - Given the following aeroplane configurations: 1. Clean wing 2. Slats only extended 3. Flaps only extended Place these configurations in order of stall angle of attack:
107 - The unit of density is:
108 - In the transonic range lift will decrease at the shock stall due to the
109 - 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:
110 - The angle between the aeroplane longitudinal axis and the chord line is the:
111 - The bank angle in a rate-one turn depends on:
112 - Which of the following statements about the stall of a straight wing aeroplane is correct?
113 - The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:
114 - Vortex generators:
115 - Which kind of boundary layer has the strongest change in velocity close to the surface?
116 - Positive static stability of an aeroplane means that following a disturbance from the equilibrium condition:
117 - What is the most effective flap system?
118 - Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
119 - An aeroplane is flying through the transonic range. As the Mach Number increases the centre of pressure of the wing will move aft. This movement requires:
120 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
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