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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 order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
2 - On a un-swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre:
3 - The stall speed:
4 - Dangerous stall characteristics, in large transport aeroplanes that require stick pushers to be installed, include:
5 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
6 - Which of the following situations leads to a decreasing stall speed (IAS)?
7 - Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
8 - Considering a positive cambered aerofoil, the pitching moment when CL = 0 is:
9 - 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?
10 - If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will
11 - Trailing edge flap extension will:
12 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim?
13 - Bernoulli's equation can be written as:(pt = total pressure, ps = static pressure, q = dynamic pressure)
14 - Load factor is:
15 - Which of the following statements about the stall of a straight wing aeroplane is correct?
16 - If the control column is pushed forward, a trim tab on the elevator:
17 - Which of the following statements about a constant speed propeller is correct?
18 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
19 - How does positive camber of an aerofoil affect static longitudinal stability?
20 - Which of the following statements about the spin is correct?
21 - Which type of stall has the largest associated angle of attack?
22 - Which statement is correct?I. Propeller gyroscopic effect occurs during aeroplane yaw changes.II. Propeller gyroscopic effect is most noticeable during low speed flight at high propeller RPM.
23 - Static lateral stability should not be too small, because:
24 - Flaperons are controls which combine the function of:
25 - 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?
26 - On a wing fitted with a 'Fowler' type trailing edge flap, the 'Full extended' position will produce:
27 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
28 - The continuity equation states: If the area of a tube is increasing, the speed of the subsonic and incompressible flow inside is
29 - A CG location beyond the aft limit leads to:
30 - 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?
31 - 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:
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 - Which statement is correct in respect of CL and angle of attack?
35 - 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:
36 - The bow wave will first appear at:
37 - 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?
38 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
39 - 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:
40 - 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):
41 - The bank angle in a rate-one turn depends on:
42 - On a swept wing aeroplane at low airspeed, the 'pitch up' phenomenon:
43 - What can happen to the aeroplane structure flying at a speed just exceeding VA ?
44 - A boundary layer fence on a swept wing will:
45 - The difference between IAS and TAS will:
46 - By what percentage does the lift increase in a level turn at 45° angle of bank, compared to straight and level flight?
47 - The angle of attack of a fixed pitch propeller blade increases when:
48 - Upon extension of a spoiler on a wing:
49 - Static lateral stability will be increased by:
50 - Rotation around the normal axis is called:
51 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
52 - The angle of attack (aerodynamic angle of incidence) of an aerofoil is the angle between the:
53 - A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:
54 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
55 - The following factors increase stall speed:
56 - In what flight phase are the outboard ailerons (if present) not operated ?
57 - The induced drag:
58 - Increasing the number of propeller blades will:
59 - 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 ?
60 - Rolling is the rotation of the aeroplane about the:
61 - Which statement about stick force per g is correct?
62 - During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection:
63 - Shock induced separation results in
64 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
65 - The critical Mach Number of an aeroplane can be increased by:
66 - 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:
67 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
68 - 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:
69 - 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:
70 - A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the:
71 - The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed:
72 - 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 ?
73 - To increase the critical Mach number a conventional aerofoil should
74 - The function of the slot between an extended slat and the leading edge of the wing is to:
75 - During an erect spin recovery:
76 - Which type of flap is shown in the picture?
question pof1.webp
77 - Which of the following statements about a Mach trimmer is correct?
78 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:
79 - In a convergent tube with an incompressible sub-sonic airflow, the following pressure changes will occur:Ps = static pressure.Pdyn = dynamic pressure. Ptot = total pressure.
80 - 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:
question pof13.webp
81 - 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)
82 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
83 - Which statement about a primary control surface controlled by a servo tab, is correct?
84 - Drag is in the direction of - and lift is perpendicular to the:
85 - What is the effect on induced drag of mass and speed changes? (all other factors of importance remaining constant)
86 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
87 - Increasing dynamic pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant):
88 - The boundary layer of a wing is:
89 - Dihedral of the wing:
90 - A slat will:
91 - The angle between the airflow (relative wind) and the chord line of an aerofoil is:
92 - The induced drag coefficient, CDi is proportional to:
93 - The application of the area rule on aeroplane design will decrease the
94 - The stall speed (IAS) will change according to the following factors:
95 - Which one of the following statements about Bernoulli's theorem is correct?
96 - A plain flap will increase CLmax by
97 - Does the pitch angle of a constant speed propeller alter in medium horizontal turbulence?
98 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
99 - Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
100 - The critical Mach number can be increased by
101 - Which kind of boundary layer has the strongest change in velocity close to the surface?
102 - Compared with the clean configuration, the angle of attack at CLmax with trailing edge flaps extended is:
103 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
104 - In twin-engine aeroplanes with right turning propellers
105 - Static pressure acts:
106 - An aeroplane has a servo tab controlled elevator. What will happen if the elevator jams during flight?
107 - When the air is passing through an expansion wave the Mach number will
108 - An engine failure can result in a windmilling ( 1) propeller and a feathered ( 2) propeller. Which statement about propeller drag is correct?
109 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
110 - The wing of an aeroplane will never stall at low subsonic speeds as long as....
111 - One advantage of a movable-stabilizer system compared with an elevator trim system is that:
112 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
113 - The stall speed increases, when: (all other factors of importance being constant)
114 - Examples of aerodynamic balancing of control surfaces are:
115 - In a steady level, co-ordinated turn, the load factor n and the stalling speed VS will be:
116 - An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:
117 - The (subsonic) static pressure:
118 - An aeroplane performs a straight and level horizontal flight at the same angle of attack at two different altitudes. (all other factors of importance being constant, assume ISA conditions and no compressibility effects)
119 - 'Flutter' may be caused by:
120 - Slat extension will:
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