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CPL Test Series
Question Bank
Questions for INDIGO AERODYNAMIC 5259-5689
Answer the following questions
Test Mode
Training Mode
1.
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
82 kt.
150 kt.
122 kt.
141 kt
2.
Which moments or motions interact in a dutch roll?
Pitching and yawing
Pitching and rolling
Rolling and yawing
Pitching and adverse yaw.
3.
The max aft position of the centre of gravity is amongst others limited by the
maximum longitudinal stability of the aeroplane
maximum elevator deflection
too small effect of the controls on the aeroplane
minimum value of the stick force per g.
4.
A plain flap will increase CLmax by
increasing angle of attack
centre of lift movement
boundary layer control.
increasing the camber of the aerofoil
5.
If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will
not change.
decrease.
increase or decrease, depends of the type of aeroplane
increase.
6.
Mcrit is the free stream Mach Number at which
Mach buffet occurs.
somewhere about the airframe Mach 1 is reached locally
the critical angle of attack is reached
shockstall occurs
7.
The boundary layer of a wing is caused by
a layer on the wing in which the stream velocity is lower than the free stream velocity, due to friction
the normal shock wave at transonic speeds
a turbulent stream pattern around the wing.
suction at the upper wing side.
8.
The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed
VD
VC
VMO
Vflutter
9.
The propeller blade angle of attack on a fixed pitch propeller is increased when
velocity and RPM decrease
forward velocity increases and RPM decreasing
RPM increases and forward velocity decreases
velocity and RPM increase
10.
The term angle of attack in a two dimensional flow is defined as
the angle between the aeroplane climb path and the horizon.
the angle between the wing chord line and the direction of the relative wind/airflow
the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing
the angle for maximum lift/drag ratio
11.
What is the correct relation of the True Air Speed (TAS) for minimum sink rate (VR/Dmin) and best glide angle (VBest glide) at a given altitude?
VR/Dmin < VBest glide
VR/Dmin = VBest glide
VR/Dmin > VBest glide
VR/Dmin > VBest glide or VR/Dmin < VBest glide depending on the type of aeroplane.
12.
On a non swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre
remains unchanged
shifts from 25% to about 50% of the aerofoil chord
slightly shifts forward
shifts aft by about 10%.
13.
Induced drag may be reduced by
a decrease of the aspect ratio
an increase in the taper ratio of the wing
the use of a wing tip with a much thinner aerofoil
an increase in aspect ratio
14.
By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
no change
19% lower
4.36% lower.
10% lower
15.
Longitudinal static stability is created by the fact that the
centre of gravity is located in front of the leading edge of the wing
aeroplane possesses a large trim speed range.
wing surface is greater than the horizontal tail surface
centre of gravity is located in front of the neutral point of the aeroplane
16.
Which statement is correct about a spring tab ?
At low IAS it behaves like a servo tab
At high IAS it behaves like a fixed extension of the elevator
At high IAS it behaves like a servo tab
Its main purpose is to increase stick force per g
17.
The additional increase of drag at Mach Numbers above the critical Mach Number is due to
increased interference drag
wave drag
increased skin friction
increased angle of attack
18.
Which statement with respect to the speed of sound is correct ?
Doubles if the temperature increases from 9° to 36° Centigrade.
Is independent of altitude
Varies with the square root of the absolute temperature.
Increases always if the density of the air decreases
19.
The bank angle in a rate-one turn depends on
weight.
wind.
load factor.
TAS.
20.
The angle between the airflow (relative wind) and the chord line of an aerofoil is
climb path angle
same as the angle between chord line and fuselage axis.
angle of attack
glide path angle
21.
The centre of gravity moving aft will
increase the elevator up effectiveness.
not affect the elevator up or down effectiveness
increase or decrease the elevator up effectiveness, depending on wing location.
decrease the elevator up effectiveness
22.
What factors determine the distance travelled over the ground of an aeroplane in a glide ?
The wind and the aeroplane's mass
The wind and weight together with power loading, which is the ratio of power output to the weight
The wind and CLmax
The wind and the lift/drag ratio, which changes with angle of attack
23.
Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
F=m / a
a=F. m
m=F.a
F=m. a
24.
Which of the following statements is correct?
A dynamically stable aeroplane would be almost impossible to fly manually
Static stability means that the aeroplane is also dynamically satble about the relevant axis.
Dynamic stability means that after being displaced from original equilibrium condition, the aeroplane will return to that condition without oscillation
Dynamic stability is possible only when the aeroplane is statically stable about the relevant axis
25.
Stick pushers must be installed in aeroplanes with dangerous stall characteristics. Dangerous stall characteristics include
Excessive wing drop and deep stall
pitch down and yaw
pitch down and increase in speed
pitch down and minor wing drop
26.
When are outboard ailerons (if present) de-activated ?
Flaps (and/or slats) extended or speed below a certain value..
Landing gear extended
Flaps (and slats) retracted or speed above a certain value.
Landing gear retracted
27.
The lift force, acting on an aerofoil
increases, proportional to the angle of attack until 40 degrees.
is mainly caused by suction on the upperside of the aerofoil.
is mainly caused by overpressure at the underside of the aerofoil
is maximum at an angle of attack of 2 degrees
28.
Propeller efficiency may be defined as the ratio between
the usable (power available) power and the maximum power
usable (power available) power of the propeller and shaft power.
the thermal power of fuel-flow and shaft power
the thrust and the maximum thrust
29.
The sensor of a stall warning system can be activated by a change in the location of the
transition region
centre of lift.
stagnation point
centre of gravity
30.
The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is
1.5
2.0
3.75
2.5
31.
Which combination of design features is known to be responsible for deep stall?
Swept back wings and a T-tail
Swept back wings and wing mounted engines
Straight wings and a T-tail
Straight wings and aft fuselage mounted engines
32.
In a twin-engined jet powered aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero ?
Down.
Up.
It depends on the position of the centre of gravity
No elevator movement will required because the thrust line of the engines remains unchanged
33.
The Cl - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the Cl - alpha graph
nowhere.
below the origin
above the origin
in the origin.
34.
Increase of wing loading will
increase the stall speeds
decrease take off speeds.
increase CLmax
decrease the minimum gliding angle.
35.
After the transition point between the laminar and turbulent boundary layer
the boundary layer gets thinner and the speed increases
the mean speed increases and the friction drag decreases
the mean speed and friction drag increases
the boundary layer gets thicker and the speed decreases
36.
Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur ?
In front of the stagnation point
In the stagnation point
Upper side
Lower side
37.
What increases the stalling angle of attack ? Use of
slats
fuselage mounted speed-brakes
spoilers
flaps
38.
The application of the area rule on aeroplane design will decrease the
skin friction drag
form drag
induced drag
wave drag
39.
In transonic flight the ailerons will be less effective than in subsonic flight because
aileron down deflection moves the shock wave forward
aileron deflection only partly affects the pressure distribution around the wing
behind the shock wave pressure is lower
aileron deflection only affects the air in front of the shock wave.
40.
In what way do (1) induced drag and (2) parasite drag alter with increasing speed?
(1) decreases and (2) increases
(1) increases and (2) increases
(1) increases and (2) decreases.
(1) decreases and (2) decreases.
41.
One of the requirements for dynamic stability is
positive static stability
effective elevator
a small C.G. range
a large deflection range of the stabilizer trim
42.
The effect of a positive wing sweep on static directional stability is as follows
No effect
Stabilizing effect
Destabilizing dihedral effect
Negative dihedral effect
43.
Which statement about a primary control surface controlled by a servo tab, is correct ?
The position is undetermined during taxiing, in particular with tailwind
The servo tab can also be used as a trimtab
The control effectiveness of the primary surface is increased by servo tab deflection
Due to the effectiveness of the servo tab the control surface area can be smaller
44.
Which one of the following statements about the dynamic stability of a conventional aeroplane about the lateral axis is correct?
An aft C.G. position shortens the period time of the phugoid.
Damping of the phugoid is normally very weak
Period time of the phugoid is normally 5 sec
Speed remains constant during one period of the phugoid.
45.
Which statement is correct about the Cl and angle of attack?
for a symmetric aerofoil, if angle of attack = 0, Cl =0
for a symmetric aerofoil, if angle of attack = 0, Cl is not equal to 0
for an asymmetric aerofoil with positive camber, if angle of attack is greater than 0, Cl = 0
for an asymmetric aerofoil, if angle of attack = 0, Cl =0
46.
The stall speed increases, when: (all other factors of importance being constant)
pulling up from a dive
minor altitude changes occur e.g. 0-10.000 ft.
weight decreases
spoilers are selected from OUT to IN.
47.
Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls ?
Servo tab
Spring tab
Balance tab
Anti-balance tab
48.
What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position ?
use the Mach trimmer until after landing.
choose a lower landing speed than normal
if possible, relocate as many passengers as possible to the front of the cabin.
choose a higher landing speed than normal and/or use a lower flapsetting for landing.
49.
An engine failure can result in a windmilling (1) propeller and a non rotating (2) propeller. Which statement about propeller drag is correct?
(1) is equal to (2).
(2) is larger than (1).
impossible to say which one is largest.
(1) is larger than (2).
50.
Deploying a Fowler flap, the flap will
just turn down
turn down, then move aft.
just move aft
move aft, then turn down
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