Discover our new portal: your complete exam preparation, enhanced by AI
Login Start Now
Mobile menu MENU
fallback
EN angle-down

Exam simulation Principles of Flight - ATPL - Airline Transport Pilot Licence

Exam simulation ATPL Question Bank in English Principles of Flight 120 questions on 120 minutes

Change Subject New Test
1 - The airload on the horizontal tailplane (tailload) of an aeroplane in straight and level flight:
2 - In an idealised steady, straight descent at 160 kt TAS and 1000 ft/min, assume that thrust is parallel to the flight path and that acceleration is zero. In this condition:
3 - For a control system in which the pilot mechanically commands only a servo tab and airflow moves the freely hinged primary surface, with no control lock engaged, what is true during taxiing at low airspeed?
4 - At fixed IAS in the ISA troposphere, neglecting instrument, position and compressibility errors, the difference TAS − IAS will:
5 - Geometric wing dihedral, viewed from the front of the aeroplane, is:
6 - The effect of a positive wing sweep on static directional stability is as follows:
7 - In the approximately linear pre-stall aerodynamic range, the aerodynamic centre of a wing is the point about which:
8 - The wing of an aeroplane will never stall at low subsonic speeds as long as....
9 - One important advantage the turbulent boundary layer has over the laminar layer is that:
10 - Which point shown in the figure corresponds with CL for minimum horizontal flight speed?
question pof7.webp
11 - 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?
12 - The Mach number:
13 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
14 - Compared with flight out of ground effect, when a wing enters ground effect at unchanged angle of attack, true airspeed and air density:
15 - With the other directional-stability and damping characteristics unchanged, what tends to increase susceptibility to weakly damped Dutch roll?
16 - The unit of density is:
17 - For a thin, unswept aerofoil in classical linear theory, as the flow regime changes from subsonic to supersonic, the aerodynamic centre approximately:
18 - In the transonic range the aeroplane characteristics are strongly determined by:
19 - In steady level flight at constant IAS and unchanged aerodynamic configuration, ignoring compressibility effects, which listed factor directly changes induced drag?
20 - For a conventional aeroplane with reversible elevator controls and natural aerodynamic stick-force feel, which statements are correct? I. Stick force per g is independent of altitude. II. Stick force per g increases as the CG moves forward.
21 - In the linear vertical-gust model, which disturbance creates a positive increment in angle of attack and load factor for an initially steady level-flying aeroplane?
22 - Which statement is correct at the speed for minimum drag (subsonic)?
23 - Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
24 - The torque effect during the take-off run in respect of a right hand propeller, when viewed from behind, will tend to:
25 - A jet transport is trimmed in steady straight-and-level flight at 1 g. Its linear manoeuvre stick-force gradient is 280 N per g and its specified positive manoeuvring limit is 2.5 g. What additional pull force is required to reach that limit?
26 - When 'spoilers' are used as speed brakes:
27 - 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:
28 - In the classical low-Mach comparison of similar, unswept, untwisted wings using the same aerofoil section, increasing aspect ratio generally has the effect of:
29 - Mach buffet occurs:
30 - If the sum of all the moments in flight is not zero, the aeroplane will rotate about the:
31 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
32 - For dry air of fixed composition in the ideal-gas approximation, which statement about the speed of sound is correct?
33 - When flaps are extended in a straight and level flight at constant IAS, the lift coefficient will eventually:
34 - Which statement about stick force per g is correct?
35 - In the usual conventional-aircraft comparison at positive lift, which list contains features that all tend to increase effective dihedral (static lateral stability)?
36 - On a wing fitted with a 'Fowler' type trailing edge flap, the 'Full extended' position will produce:
37 - At unchanged mass and configuration, how can indicated stall speed vary with altitude, if compressibility becomes significant at high altitude?
38 - In the classical comparison of untwisted wings with comparable span, area and aerofoil section at low Mach number and equal overall lift, which listed planform has the greatest root section lift coefficient?
39 - For a conventional aerofoil producing positive lift at normal pre-stall angles of attack, the lift force:
40 - For a conventional twin-engine aeroplane with both propellers turning clockwise as viewed from the pilot’s seat, under power at positive angle of attack:
41 - 'Tuck under' is:
42 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
43 - An advantage of locating the engines at the rear of the fuselage, in comparison to a location beneath the wing, is:
44 - In classical linear thin-aerofoil theory, with geometry and lift-curve slope otherwise unchanged, how does the constant pitching-moment coefficient caused by positive camber directly affect static longitudinal stability?
45 - Which adverse aerodynamic effects have been observed in tests of a wing exposed to very heavy rain?
46 - For an intact aeroplane, a single large up-elevator input at a speed just above the applicable manoeuvring speed VA creates which structural risk?
47 - The maximum aft position of the centre of gravity is, amongst others, limited by the:
48 - What is the advantage of a variable incidence tailplane over a fixed incidence tailplane with elevator and trim tab?
49 - Examples of aerodynamic balancing of control surfaces are:
50 - Static pressure acts:
51 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
52 - On an aeroplane whose approved take-off retraction sequence keeps slats extended after the trailing-edge flaps are retracted, what is the main aerodynamic benefit?
53 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
54 - In the classical fixed-area wing model, extending only the inboard trailing-edge flaps at constant IAS and total wing lift allows angle of attack to be reduced. Assuming attached flow and unchanged outboard aerofoil characteristics, the lift on the unflapped outer wing sections will normally:
55 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
56 - Which statement follows from Bernoulli's equation for incompressible flow when total pressure remains constant?
57 - Long period (phugoid) oscillations are characterised by:
58 - Which statement is correct about a spring tab?
59 - A boundary layer fence on a swept wing will:
60 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
61 - In the representative manoeuvring V-n structural-design diagram of CS 25.333(b), which speed forms the extreme right-hand boundary?
62 - Tuck under will happen
63 - 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?
64 - For steady incompressible flow, total pressure is: (ρ = local fluid density)
65 - One disadvantage of a simple unmodified swept-back wing is its stall tendency. As the stall develops:
66 - Which aeroplane design has the highest probability of a super stall?
67 - Which statement correctly describes a mass-distribution measure used in the design against wing bending-torsion flutter?
68 - The high lift device shown in the figure is a:
question pof4.webp
69 - A high aspect ratio wing produces:
70 - Which one of the bodies in motion (all bodies have the same cross section area) will have lowest drag?
question pof2.webp
71 - An aeroplane performs a steady horizontal turn with a TAS of 200 KT. The turn radius is 2000m. The load factor (n) is approximately:
72 - The unit of measurement of pressure is:
73 - The induced drag coefficient, CDi is proportional to:
74 - Where a powered-control system uses aerodynamic tab assistance for manual reversion after hydraulic failure, which listed tab type performs that function?
75 - Which of the following statements concerning control is correct?
76 - The 'short period mode' is an:
77 - In steady level flight at constant IAS and unchanged aerodynamic configuration, ignoring compressibility, induced drag is directly affected by:
78 - In steady level flight (weight, altitude and configuration constant), an increase of dynamic pressure has the following effect on the total drag of an aeroplane:
79 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move
80 - Which statement is correct in respect of CL and angle of attack?
81 - In a steady level, co-ordinated turn, the load factor n and the stalling speed VS will be:
82 - For a conventional aeroplane whose tail supplies a balancing downforce and whose thrust contributes to lift or vertical support, which listed group of changes tends to increase stall speed?
83 - A jet has inboard and outboard ailerons, with the outboard ailerons locked out in the high-speed cruise configuration. Which ailerons are active in that configuration?
84 - In an idealised level-flight model, the wing lift acts ahead of the CG and the horizontal tail is behind the CG. Neglect all other pitching moments. For pitching-moment balance, the tail force must act:
85 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
86 - 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:
87 - Which of the following statements about a Mach trimmer is correct?
88 - Which listed stall condition is associated with very high angles of attack that can immerse a susceptible T-tail in the wing wake and make pitch recovery ineffective?
89 - The boundary layer of a wing is:
90 - 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:
91 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
92 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
93 - How are the speeds (shown in the figure) at point 1 and point 2 related to the relative wind / airflow V?
question pof6.webp
94 - At unchanged controls and dynamic pressure, with a positive lift-curve slope, which is the aerodynamic criterion for static longitudinal stability of the aeroplane?
95 - The stalling speed in IAS will change according to the following factors:
96 - If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes? (low speed, subsonic and incompressible flow)
97 - Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
98 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
99 - On a transport aeroplane fitted with a conventional high-speed lockout for its low-speed outboard ailerons, inhibition is normally associated with:
100 - The terms 'q' and 'S' in the lift formula are:
101 - In a linear incompressible model of a swept-wing aeroplane at unchanged dynamic pressure, lift coefficient and configuration, ignore Mach effects and assume that the aerodynamic coefficients remain unchanged. As altitude and TAS increase, static lateral stability (1) and natural aerodynamic roll/yaw damping (2) will:
102 - The formula for the Mach Number is: (a= speed of sound)
103 - In a conventional low-wing aeroplane model, assume that flap extension adds a nose-down pitching moment, the tail supplies balancing downforce, and changes in tail downwash and dynamic pressure are neglected. During landing, which combination requires the greatest up-elevator deflection for balance?
104 - Positive static lateral stability is the tendency of an aeroplane to:
105 - Induced drag is created by the:
106 - 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?
107 - The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from:
108 - VMO:
109 - A line connecting the leading edge and trailing edge midway between the upper and lower surface of an aerofoil. This definition is applicable for:
110 - For the classical comparison of the same conventional aerofoil with 1. no high-lift device, 2. only a leading-edge slat opening a slot, and 3. only a plain trailing-edge flap, place the configurations in order of increasing stall angle of attack:
111 - The angle of attack of a blade section is the angle between the chord line and the:
112 - The (subsonic) static pressure:
113 - Under CS25.341(a)(5)(i), which combination gives the sea-level reference gust velocity (EAS) and a design speed at which it applies, for the clean configuration?
114 - 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:
115 - During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)
116 - Under CS25.337(b), what is the minimum positive manoeuvring limit load factor in the clean configuration for a transport aeroplane with a design maximum take-off weight of at least 50,000 lb?
117 - The most important problem of ice accretion on a transport aeroplane during flight is:
118 - For a conventional aerofoil at unchanged dynamic pressure, increasing angle of attack just beyond the angle of CLmax into the stall normally causes lift (1) and drag (2), compared with the values at CLmax, to:
119 - In a first-order sideslip model, a symmetrical ventral fin on the centreline lies behind and below the CG. Neglecting secondary interference effects, its contribution to static stability is: (1 = longitudinal, 2 = lateral, 3 = directional)
120 - In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack must be:
3 Days
Free Trial
No Payment Required
No Subscription
Start for free
PRO
★★★★★ 4,7/5
Quizvds PRO
All Questions Included
View portal plans
Subscribe to Newsletter
Sign up, it's free
Download mobile apps
Google Play App Store
© 2026 EGWeb di Guatta Mattia - VAT: 04768540983