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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 - In which situation would the wing lift of an aeroplane in straight and level flight have the highest value?
2 - The lift force, acting on an aerofoil:
3 - Which statement is correct about a normal shock wave?
4 - The trailing edge flaps when extended:
5 - The angle of attack of a wing profile is defined as the angle between:
6 - In twin-engine aeroplanes with right turning propellers
7 - Which point shown in the figure corresponds with CL for minimum horizontal flight speed?
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8 - When a jet transport aeroplane takes off with the CG at the forward limit and the trimmable horizontal stabiliser (THS) is positioned at the maximum allowable nose up position for take- off:
9 - One important advantage the turbulent boundary layer has over the laminar layer is that:
10 - 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?
11 - VMO:
12 - The stall speed in a 60° banked turn increases by the following factor:
13 - Considering a positive cambered aerofoil, the pitching moment when CL = 0 is:
14 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
15 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
16 - Which design features improve static lateral stability? 1. Anhedral. 2. Dihedral. 3. Forward sweep. 4. Sweepback. The combination that regroups all of the correct statements is:
17 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
18 - Which of the following statements about boundary layers is correct?
19 - The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the:
20 - Vortex generators on the upper side of the wing surface will:
21 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
22 - Load factor is:
23 - If the elevator trim tab is deflected up, the cockpit trim indicator presents:
24 - A boundary layer fence on a swept wing will:
25 - A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:
26 - Spoiler deflection causes:
27 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
28 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
29 - Tuck under will happen
30 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
31 - Bernoulli's equation can be written as: (pt= total pressure, ps = static pressure and q=dynamic pressure)
32 - Trailing edge flap extension will:
33 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
34 - Which of the following statements about dihedral is correct?
35 - A slotted flap will increase the CLmax by:
36 - What data may be obtained from buffet onset boundary data?
37 - When the air has passed through a normal shock wave the Mach number is
38 - 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)
39 - The 'short period mode' is an:
40 - The induced angle of attack is the result of:
41 - The relationship between induced drag and the aspect ratio is:
42 - In case the Mach trimmer fails:
43 - Induced drag is created by the:
44 - The lift- and drag forces, acting on a wing cross section:
45 - Static lateral stability will be increased by:
46 - The aeroplane drag in straight and level flight is lowest when the:
47 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls?
48 - The following unit of measurement: kg m/s^2 is expressed in the SI-system as:
49 - Assuming ISA conditions, which statement with respect to the climb is correct?
50 - The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is:
51 - Deploying a Fowler flap, the flap will:
52 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position?
53 - Increasing dynamic pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant):
54 - The angle of attack of a blade section is the angle between the chord line and the:
55 - The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:
56 - 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?
57 - The effect of a ventral fin on the static stability of an aeroplane is as follows: (1=longitudinal, 2=lateral, 3=directional)
58 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
59 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
60 - If the trailing edge flaps are lowered (fully extended), in order to maintain constant IAS and level flight:
61 - Positive static lateral stability is the tendency of an aeroplane to:
62 - The SI units of air density (I) and force (II) are:
63 - In a stationary subsonic streamline flow pattern, if the streamlines converge, in this part of the pattern, the static pressure (I) will... and the velocity (II) will...:
64 - In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack must be:
65 - The manoeuvrability of an aeroplane is best when the:
66 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move
67 - During a climb at a constant IAS, the Mach Number:
68 - Which statement is correct about a spring tab?
69 - A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the:
70 - An aeroplane is provided with spoilers and in- and outboard ailerons. Roll control during cruise is provided by:
71 - When the air is passing through a shock wave the static temperature will
72 - The function of the stick pusher is:
73 - Vortex generators:
74 - During a phugoid the speed:
75 - Shock induced separation results in
76 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42. An increase in angle of attack of 1 degree increases CL by 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be:
77 - An example of differential aileron deflection during initiation of left turn is:
78 - Induced drag may be reduced by:
79 - The bow wave will first appear at:
80 - The effect of a positive wing sweep on static directional stability is as follows:
81 - The (1) stick force stability and the (2) manoeuvre stability are positively affected by:
82 - The loss of total pressure in a shock wave is due to the fact that
83 - What will happen in ground effect?
84 - If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less than wing span)
85 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
86 - 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:
87 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
88 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
89 - An aeroplane has a stall speed of 100 kt at a mass of 1000 kg. If the mass is increased to 2000 kg, the new value of the stall speed will be:
90 - Washout is:
91 - On a wing fitted with a 'Fowler' type trailing edge flap, the 'Full extended' position will produce:
92 - Assuming ISA conditions, climbing at a constant Mach Number up to FL 350 the TAS will:
93 - Rotation around the normal axis is called:
94 - 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:
95 - During the retraction of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant):
96 - One method to compensate adverse yaw is:
97 - When power assisted controls are used for pitch control:
98 - Which of the following statements about the stall of a straight wing aeroplane is correct?
99 - Rotation about the lateral axis is called:
100 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
101 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
102 - What will increase the sensitivity to Dutch Roll?
103 - Which of the following wing planforms gives the highest local lift coefficient at the wing root?
104 - Which kind of boundary layer has the strongest change in velocity close to the surface?
105 - The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
106 - The critical Mach Number of an aeroplane can be increased by:
107 - The critical angle of attack:
108 - Which of the following statements about the spin is correct?
109 - The angle of attack for a propeller blade is the angle between the blade chord line and the:
110 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
111 - 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)
112 - Critical Mach number is the free stream Mach number at which:
113 - What is the advantage of a variable incidence tailplane over a fixed incidence tailplane with elevator and trim tab?
114 - The CG of an aeroplane is in a fixed position forward of the neutral point. Which of these statements about the stick force stability is correct?
115 - When the air is passing through an expansion wave the Mach number will
116 - 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:
117 - 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:
118 - 1. When the mass decreases, the gust load factor increases. 2. The gust load increases, when the altitude increases.
119 - The induced drag:
120 - An aeroplane is descending at a constant Mach number from FL 350. What is the effect on true airspeed?
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