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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 - After the transition point between the laminar and turbulent boundary layer
2 - Which load factor determines VA?
3 - In straight and level flight, as speed is increased:
4 - The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:
5 - The pitch up effect of an aeroplane with swept wing in a stall is due to the
6 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is:
7 - 'Tuck under' is caused by (i) which movement of the centre of pressure of the wing and (ii) which change of the downwash angle at the location of the stabilizer.
8 - 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?
9 - The critical angle of attack:
10 - A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor:
11 - Induced drag may be reduced by:
12 - The lift formula is:
13 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
14 - Bernoulli's equation can be written as:(pt = total pressure, ps = static pressure, q = dynamic pressure)
15 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
16 - Examples of aerodynamic balancing of control surfaces are:
17 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:
18 - Which type of stall has the largest associated angle of attack?
19 - 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:
20 - The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:
21 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
22 - The induced drag:
23 - In a twin engine jet aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero ?
24 - The SI units of air density (I) and force (II) are:
25 - 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?
26 - Winglets
27 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
28 - Which of the following statements about a Mach trimmer is correct?
29 - 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:
30 - Which combination of design features is known to be responsible for deep stall?
31 - In what way do ( 1) induced drag and ( 2) parasite drag alter with increasing speed in straight and level flight?
32 - What is the SI unit of measurement for power?
33 - Which statement about a primary control surface controlled by a servo tab, is correct?
34 - The critical Mach number can be increased by
35 - Vortex generators on the upper side of the wing:
36 - The 'short period mode' is an:
37 - What is the purpose of an auto-slat system?
38 - Rotation around the normal axis is called:
39 - When the air is passing through an expansion wave the Mach number will
40 - On a wing fitted with a 'Fowler' type trailing edge flap, the 'Full extended' position will produce:
41 - The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of:
42 - What factors determine the distance travelled over the ground of an aeroplane in a glide ?
43 - The gust load increases, when the altitude increases.
44 - After take-off the slats (when installed) are always retracted later than the flaps. Why?
45 - The difference between IAS and TAS will:
46 - The angle of attack of a blade section is the angle between the chord line and the:
47 - Ground effect has the following influence on the landing distance:
48 - The terms 'q' and 'S' in the lift formula are:
49 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
50 - 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:
51 - By what percentage does the lift increase in a level turn at 45° angle of bank, compared to straight and level flight?
52 - What data may be obtained from the Buffet Onset Boundary chart?
53 - When the air has passed through a normal shock wave the Mach number is
54 - Does the pitch angle of a constant speed propeller alter in medium horizontal turbulence?
55 - A laminar boundary layer is a layer, in which:
56 - An aeroplane is provided with spoilers and in- and outboard ailerons. Roll control during cruise is provided by:
57 - Which of the following aeroplane parts affect induced drag most?
58 - Vortex generators on the upper side of the wing surface will:
59 - If the control column is pushed forward, a trim tab on the elevator:
60 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim?
61 - Increase of wing loading will:
62 - Mach buffet occurs:
63 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
64 - The units of wing loading (I) W / S and (II) dynamic pressure q are:
65 - The maximum aft position of the centre of gravity is, amongst others, limited by the:
66 - 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 ?
67 - The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:
68 - Washout is:
69 - The application of the area rule on aeroplane design will decrease the
70 - A plain flap will increase CLmax by
71 - Which of the following statements about the difference between Krueger flaps and slats is correct?
72 - The relationship between induced drag and the aspect ratio is:
73 - Which definition of propeller parameters is correct?
74 - One advantage of a movable-stabilizer system compared with an elevator trim system is that:
75 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
76 - Considering a positive cambered aerofoil, the pitching moment when CL = 0 is:
77 - If in a two-dimensional incompressible and subsonic flow, the streamlines converge the static pressure in the flow will:
78 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
79 - Spoiler deflection causes:
80 - Which one of the bodies in motion (all bodies have the same cross section area) will have lowest drag?
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81 - The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
82 - If the nose of an aeroplane yaws left, this causes:
83 - Which statement is correct regarding a shockwave on a lift generating wing?
84 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
85 - VLE is defined as the:
86 - The lift force, acting on an aerofoil:
87 - The correct drag formula is:
88 - 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)
89 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
90 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
91 - Static lateral stability will be increased by:
92 - 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:
93 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
94 - The loss of total pressure in a shock wave is due to the fact that
95 - An aeroplane, being manually flown in the speed unstable region, experiences a disturbance that causes a speed reduction.If the altitude is maintained and thrust remains constant, the aeroplane speed will:
96 - The effect of a positive wing sweep on static directional stability is as follows:
97 - 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?
98 - Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
99 - When flaps are deployed at constant angle of attack the lift coefficient will:
100 - Low speed pitch up is caused by the:
101 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
102 - The high lift device shown in the figure below is a:
question pof5.webp
103 - The Mach number:
104 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
105 - If the elevator trim tab is deflected up, the cockpit trim indicator presents:
106 - How does stalling speed (IAS) vary with altitude?
107 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
108 - During a climb at a constant IAS, the Mach Number:
109 - Which of the following wing planforms gives the highest local lift coefficient at the wing root?
110 - The consequences of exceeding Mcrit in a swept-wing aeroplane may be: (assume no corrective devices, straight and level flight)
111 - A slotted flap will increase the CLmax by:
112 - The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
113 - If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will
114 - Which of the following ( 1) aerofoils and ( 2) angles of attack will produce the lowest Mcrit values?
115 - When trailing edge flaps are selected down whilst maintaining straight and level flight at constant IAS:
116 - Critical Mach number is the free stream Mach number at which:
117 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position ?
118 - The stall speed:
119 - In a steady level, co-ordinated turn, the load factor n and the stalling speed VS will be:
120 - Deflection of leading edge flaps will:
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