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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 - 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)
2 - A boundary layer fence on a swept wing will:
3 - When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be:
4 - The torque effect during the take off run in respect of a right hand propeller, when viewed from behind, will tend to:
5 - Critical Mach number is the free stream Mach number at which:
6 - What is the SI unit of measurement for power?
7 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
8 - Just above the critical Mach number the first evidence of a shock wave will appear at the
9 - In case the Mach trimmer fails:
10 - The lift formula is:
11 - A plain flap will increase CLmax by
12 - When the air is passing through an expansion wave the static temperature will
13 - An aeroplane is provided with spoilers and in- and outboard ailerons. Roll control during cruise is provided by:
14 - What is the most effective flap system?
15 - 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?
16 - 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:
17 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
18 - An aeroplane has a stalling speed of 100 KT in a steady level flight. When the aeroplane is flying a level turn with a load factor of 1.5, the stalling speed is:
19 - One important advantage the turbulent boundary layer has over the laminar layer is that:
20 - Load factor is:
21 - The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
22 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position ?
23 - The function of the slot between an extended slat and the leading edge of the wing is to:
24 - What data may be obtained from the Buffet Onset Boundary chart?
25 - Assuming no compressibility effects, induced drag at constant IAS is affected by:
26 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
27 - Which statement is correct for a side slip condition at constant speed and side slip angle, where the geometric dihedral of an aeroplane is increased ?
28 - 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?
29 - Total pressure is: (rho = density)
30 - The 'short period mode' is an:
31 - Which one of the bodies in motion (all bodies have the same cross section area) will have lowest drag?
question pof2.webp
32 - At higher altitudes, the stall speed (IAS):
33 - The aft movement of the centre of pressure during acceleration through the transonic range will:
34 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
35 - An example of differential aileron deflection during initiation of left turn is:
36 - Washout is:
37 - Which type of stall has the largest associated angle of attack?
38 - Which of the following aeroplane parts affect induced drag most?
39 - The SI units of air density (I) and force (II) are:
40 - The boundary layer of a wing is:
41 - The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are:
42 - The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately:
43 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
44 - Induced drag at constant IAS is affected by:
45 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
46 - The pitch up effect of an aeroplane with swept wing in a stall is due to the
47 - To be able to predict compressibility effects you have to determine the:
48 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
49 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls ?
50 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
51 - The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
52 - The stall speed in a 60° banked turn increases by the following factor:
53 - The sensor of a stall warning system can be activated by a change in the location of the
54 - Drag is in the direction of - and lift is perpendicular to the:
55 - The angle between the airflow (relative wind) and the chord line of an aerofoil is:
56 - What increases the stalling angle of attack ? Use of:
57 - 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:
58 - The trailing edge flaps when extended:
59 - In the transonic range the aeroplane characteristics are strongly determined by:
60 - By what percentage does the lift increase in a level turn at 45° angle of bank, compared to straight and level flight?
61 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
62 - The critical Mach Number of an aeroplane can be increased by:
63 - Which statement is correct?The lift to drag ratio determines the
64 - Deploying a Fowler flap, the flap will:
65 - Which of the following flight phenomena can occur at Mach numbers below the critical Mach number?
66 - The CL - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the CL- alpha graph:
67 - Compared with level flight prior to the stall, the lift ( 1) and drag ( 2) in the stall change as follows:
68 - Examples of aerodynamic balancing of control surfaces are:
69 - If in a two-dimensional incompressible and subsonic flow, the streamlines converge the static pressure in the flow will:
70 - The pitching moment versus angle of attack line in the diagram, which corresponds to a CG located at the neutral point of of a given aeroplane at low and moderate angles of attack is:
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71 - 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:
72 - The lift formula is: (rho = density)
73 - During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)
74 - 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:
75 - Which of the following statements about a Mach trimmer is correct?
76 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
77 - Assuming ISA conditions, climbing at a constant Mach Number up to FL 350 the TAS will:
78 - Which of the following statements about a constant speed propeller is correct?
79 - Positive static longitudinal stability means that a:
80 - Upon extension of a spoiler on a wing:
81 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
82 - The terms 'q' and 'S' in the lift formula are:
83 - Which statement is correct in respect of CL and angle of attack?
84 - Which line represents the total drag line of an aeroplane?
question pof9.webp
85 - The induced angle of attack is the result of:
86 - Vortex generators on the upper side of the wing surface will:
87 - Dihedral of the wing is:
88 - The angle between the aeroplane longitudinal axis and the chord line is the:
89 - The aspect ratio of the wing:
90 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ?
91 - Positive static stability of an aeroplane means that following a disturbance from the equilibrium condition:
92 - A CG location beyond the aft limit leads to:
93 - Which statement is correct at the speed for minimum drag (subsonic) ?
94 - The angle of attack of a wing profile is defined as the angle between:
95 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
96 - A jet aeroplane cruises buffet free at high constant altitude. Which type of stall can occur if this aeroplane decelerates during an inadvertent increase in load factor?
97 - Induced drag may be reduced by:
98 - The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:
99 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
100 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move
101 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
102 - A "slat" is:
103 - Mach buffet occurs:
104 - The effect of a positive wing sweep on static directional stability is as follows:
105 - For an aeroplane with one fixed value of VA the following applies. VA is:
106 - The true airspeed (TAS) is:
107 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
108 - The induced drag coefficient, CDi is proportional to:
109 - An aeroplane has a servo tab controlled elevator. What will happen if the elevator jams during flight?
110 - Which statement about induced drag and tip vortices is correct?
111 - When are outboard ailerons (if present) de-activated?
112 - The high lift device shown in the figure is a:
question pof4.webp
113 - When the air has passed through a normal shock wave the Mach number is
114 - If an aeroplane exhibits insufficient stick force per g, this problem can be resolved by installing:
115 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
116 - The lift force, acting on an aerofoil:
117 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes:
118 - The unit of density is:
119 - One advantage of a movable-stabilizer system compared with an elevator trim system is that:
120 - When flaps are deployed at constant angle of attack the lift coefficient will:
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