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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 - Which type of flap is shown in the picture?
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2 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
3 - The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately:
4 - Drag is in the direction of - and lift is perpendicular to the:
5 - In what flight phase are the outboard ailerons (if present) not operated?
6 - 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
7 - What increases the stalling angle of attack? Use of:
8 - Which kind of boundary layer has the strongest change in velocity close to the surface?
9 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
10 - Vortex generators on the upper side of the wing surface will:
11 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
12 - The trailing edge flaps when extended:
13 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
14 - Shock induced separation results in
15 - The angle of attack of a two dimensional wing section is the angle between:
16 - 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):
17 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
18 - What wing shape or wing characteristic is the least sensitive to turbulence:
19 - Mcrit is the free stream Mach Number at which:
20 - Rolling is the rotation of the aeroplane about the:
21 - The effect of a positive wing sweep on static directional stability is as follows:
22 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:
23 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
24 - Which of the following statements about the stall of a straight wing aeroplane is correct?
25 - On a wing fitted with a 'Fowler' type trailing edge flap, the 'Full extended' position will produce:
26 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. An increase in angle of attack of 1 degree would increase CL by 0.079. If a vertical gust instantly changes the angle of attack by 2 degrees, the load factor will be:
27 - The critical Mach number can be increased by
28 - Bernoulli's equation can be written as: (pt = total pressure, ps = static pressure, q = dynamic pressure)
29 - When an aeroplane is flying at an airspeed which is 1.3 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be:
30 - Assuming no compressibility effects, induced drag at constant IAS is affected by:
31 - 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?
32 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
33 - Which has the effect of increasing load factor? (all other relevant factors being constant)
34 - An advantage of locating the engines at the rear of the fuselage, in comparison to a location beneath the wing, is:
35 - Which statement is correct at the speed for minimum drag (subsonic)?
36 - Slat extension will:
37 - The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the:
38 - The true airspeed (TAS) is:
39 - Which of the following aeroplane parts affect induced drag most?
40 - Which of the following statements about the spin is correct?
41 - What is the purpose of an auto-slat system?
42 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability?
43 - When are outboard ailerons (if present) de-activated?
44 - An engine failure can result in a windmilling (1) propeller and a feathered (2) propeller. Which statement about propeller drag is correct?
45 - The relative thickness of an aerofoil is expressed as:
46 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
47 - The induced drag:
48 - 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?
49 - 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:
50 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
51 - One important advantage the turbulent boundary layer has over the laminar layer is that:
52 - Which one of the following statements about Bernoulli's theorem is correct?
53 - Which of the following statements about a constant speed propeller is correct?
54 - 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:
55 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
56 - The relationship between the stall speed VS and VA (EAS) for a large transport aeroplane can be expressed in the following formula: (SQRT= square root)
57 - 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:
58 - The Mach number:
59 - Assuming ISA conditions, climbing at a constant Mach Number up to FL 350 the TAS will:
60 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
61 - The aspect ratio of the wing:
62 - With increasing angle of attack, the stagnation point will move (I) ... and the point of lowest pressure will move (II) ... Respectively (I) and (II) are:
63 - Which phenomenon is counteracted with differential aileron deflection?
64 - The (1) stick force stability and the (2) manoeuvre stability are positively affected by:
65 - Positive static lateral stability is the tendency of an aeroplane to:
66 - Assuming an initial condition in straight and level flight with CL = 1. What will be the new value of CL after the value of the speed has doubled?
67 - The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with:
68 - Which load factor determines VA?
69 - Bernoulli's equation can be written as: (pt= total pressure, ps = static pressure and q=dynamic pressure)
70 - Which statement is correct in respect of CL and angle of attack?
71 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
72 - Total pressure is: (rho = density)
73 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
74 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
75 - A high aspect ratio wing produces:
76 - Induced drag may be reduced by:
77 - A boundary layer fence on a swept wing will:
78 - The bow wave will first appear at:
79 - The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:
80 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
81 - Static pressure acts:
82 - An aeroplane is descending at a constant Mach number from FL 350. What is the effect on true airspeed?
83 - Which combination of design features is known to be responsible for deep stall?
84 - Which statement with respect to the speed of sound is correct?
85 - Assuming ISA conditions, which statement with respect to the climb is correct?
86 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls?
87 - 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?
88 - If you pull back the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
89 - Which line represents the total drag line of an aeroplane?
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90 - 'Tuck under' may happen at:
91 - 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:
92 - Which statement is correct regarding a shockwave on a lift generating wing?
93 - The value of the manoeuvre stability of an aeroplane is 150 N / g. The stick force required to achieve a load factor of 2.5 from steady level flight is:
94 - An aeroplane transitions from steady straight and level flight into a horizontal co-ordinated turn with a load factor of 2, the speed remains constant and the:
95 - Critical Mach number is the free stream Mach number at which:
96 - What is the most effective flap system?
97 - Which aeroplane design has the highest probability of a super stall?
98 - When 'spoilers' are used as speed brakes:
99 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
100 - When the air has passed through a normal shock wave the Mach number is
101 - The lift- and drag forces, acting on a wing cross section:
102 - Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
103 - To increase the critical Mach number a conventional aerofoil should
104 - The induced angle of attack is the result of:
105 - 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?
106 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
107 - The bank angle in a rate-one turn depends on:
108 - Which statement about stick force per g is correct?
109 - What factors determine the distance travelled over the ground of an aeroplane in a glide?
110 - To be able to predict compressibility effects you have to determine the:
111 - In twin-engine aeroplanes with right turning propellers
112 - If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
113 - The angle between the airflow (relative wind) and the chord line of an aerofoil is:
114 - When a pilot makes a turn in horizontal flight, the stall speed:
115 - Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?
116 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
117 - The high lift device shown in the figure below is a:
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118 - For an aeroplane with one fixed value of VA the following applies. VA is:
119 - In what way do (1) induced drag and (2) parasite drag alter with increasing speed in straight and level flight?
120 - During an erect spin recovery:
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