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CPL Test Series
Question Bank
Questions for INDIGO AERODYNAMIC 5259-5689
Answer the following questions
Test Mode
Training Mode
1.
If an aeroplane flies in the ground effect
the induced angle of attack is increased
drag and lift are reduced.
the effective angle of attack is decreased.
the lift is increased and the drag is decreased.
2.
Why is a propeller blade twisted from root to tip?
To ensure that the root produces most thrust.
To ensure that the tip produces most thrust.
Because the local angle of attack of a blade segment is dependent on the ratio of that segment 's speed in the plane of rotation and the true airspeed of the aeroplane
Because the local angle of attack of a blade segment is dependent on the ratio of that segment 's speed in the plane of rotation and the angular velocity of the propellers
3.
One advantage of a movable-stabilizer system compared with a fixed stabilizer system is that
the system's complexity is reduced
the structure weighs less
it is a more powerful means of trimming
it leads to greater stability in flight
4.
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
5.
The following factors increase stall speed
a higher weight, selecting a higher flap setting, a forward c .g. shift.
a lower weight, decreasing bank angle, a smaller flapsetting
increasing bank angle, increasing thrust, slat extension.
an increase in load factor, a forward c.g. shift, decrease in thrust.
6.
A jet aeroplane is rolled into a turn, while maintaining airspeed and holding altitude. In such a case, the pilot has to
increase angle of attack and keep thrust unchanged.
increase thrust and decrease angle of attack
increase thrust and angle of attack
increase thrust and keep angle of attack unchanged.
7.
Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
fit the engine intakes better to the fuselage
improve the low speed characteristics
increase the strength of the wing root junction.
apply area rule.
8.
Increase of wing loading will
decrease the minimum gliding angle.
decrease take off speeds.
increase CLmax
increase the stall speeds
9.
The relationship between the stall speed VS and VA (EAS) for a large transport aeroplane can be expressed in the following formula:(SQRT= square root)
VA= VS SQRT(2.5)
VS= VA SQRT(3.75)
Va= VA SQRT(3.75)
VS= VA SQRT(2.5)
10.
A normal shock wave
can occur at different points on the aeroplane in transonic flight.
is a discontinuity plane in an airflow, in which the pressure drops suddenly
is a discontinuity plane in an airflow, which is always normal to the surface
is a discontinuity plane in an airflow, in which the temperature drops suddenly.
11.
The aerodynamic centre of the wing is the point, where
change of lift due to variation of angle of attack is constant
aerodynamic forces are constant
pitching moment coefficient does not vary with angle of attack
the aeroplane's lateral axis intersects with the centre of gravity
12.
Floating due to ground effect during an approach to land will occur
at a speed approaching the stall
when the height is less than halve of the length of the wing span above the surface
when the height is less than twice the length of the wing span above the surface
when a higher than normal angle of attack is used
13.
Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
F=m. a
a=F. m
F=m / a
m=F.a
14.
What happens during an engine failure with two similar aeroplanes with wing mounted engines, one of them with jet engines, the other one with co-rotating propellers
The same roll tendency for both aeroplanes
More roll tendency for the propeller aeroplane
Less roll tendency for the propeller aeroplane
The same yaw tendency for both aeroplanes regardless of left or right engine failure.
15.
Which of the following statements about dihedral is correct?
Effective dihedral is the angle between the 1/4-chord line and the lateral axis of the aeroplane
Dihedral is necessary for the execution of slip-free turns
Dihedral contributes to dynamic but not to static lateral stability
The ""effective dihedral"" of an aeroplane component means the contribution of that component to the static lateral stability
16.
The turn indicator shows a right turn. The slip indicator is left of neutral. To coordinate the turn
a higher turn rate is required.
less right bank is required.
more right rudder is required
more right bank is required
17.
The effect of a high wing with zero dihedral is as follows
Its only purpose is to ease aeroplane loading
Positive dihedral effect
Negative dihedral effect
Zero dihedral effect
18.
Which location on the aeroplane has the largest effect on the induced drag ?
Wing root junction
Engine cowling
Wing tip
Landing gear
19.
The unit of density is
psi
kg/cm²
kg/m³
Bar
20.
The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with
1/V
V²
V
1/V²
21.
The total pressure is
½ rho V²
can be measured in a small hole in a surface, parallel to the local stream.
static pressure minus the dynamic pressure
static pressure plus the dynamic pressure
22.
The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is
450 N.
225 N.
150 N.
375 N.
23.
Which aeroplane design has the highest probability of a super stall?
A low horizontal tail
A canard wing
Swept wings
A T-tail
24.
Which statement is correct about the Cl and angle of attack?
for an asymmetric aerofoil, if angle of attack = 0, Cl =0
for an asymmetric aerofoil with positive camber, if angle of attack is greater than 0, Cl = 0
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
25.
The lift- and drag forces, acting on a wing cross section
vary linearly with the angle of attack
are proportional to each other, independent of angle of attack
are normal to each other at just one angle of attack
depend on the pressure distribution about the wing cross section.
26.
If the Mach number of an aeroplane in supersonic flight is increased, the shock wave angles will
decrease and beyond a certain Mach number start increasing again.
increase.
decrease.
stay constant
27.
What is the effect on induced drag of weight and speed changes ?
induced drag increases with increasing speed and induced drag increases with decreasing weight
induced drag decreases with increasing speed and induced drag decreases with decreasing weight
induced drag increases with decreasing speed and induced drag increases with increasing weight
induced drag decreases with decreasing speed and induced drag decreases with increasing weight
28.
Increasing the number of propeller blades will
increase the noise level at maximum power
increase the maximum absorption of power
decrease the torque in the propeller shaft at maximum power
increase the propeller efficiency
29.
Which statement about a jet transport aeroplane is correct, during take-off at the maximum allowable forward centre of gravity limit, while the THS (Trimmable Horizontal Stabilizer) has been positioned at the maximum allowable AND (Aeroplane Noise Down) position
Early nose wheel raising will take place.
Nothing special will happen.
The rotation will require extra stick force
If the THS position is just within the limits of the green band, the take off warning system will be activated
30.
The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
the chord of a large rectangular wing
the average chord of the actual aeroplane
the chord of a rectangular wing with same moment and lift
the wing area divided by the wing span
31.
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)
the TAS at the higher altitude cannot be determined
the TAS at both altitudes is the same
the TAS at the higher altitude is higher
the TAS at the higher altitude is lower
32.
Increasing air pressure will have the following effect on the drag of an aeroplane (angle of attack, OAT and TAS are constant)
The drag is only affected by the ground speed.
The drag decreases
This has no effect
The drag increases
33.
What is the most effective flap system?
Fowler flap
Plain flap
Single slotted flap
Split flap.
34.
With increasing altitude and constant IAS the static lateral stability (1) and the dynamic lateral/directional stability (2) of an aeroplane with swept-back wing will
(1) decrease (2) increase
(1) increase (2) increase
(1) decrease (2) decrease.
(1) increase (2) decrease.
35.
Dihedral of the wing
increases the static lateral stability
is the only way to increase the static lateral stability
is only positive for aeroplanes with high mounted wings.
decreases the static lateral stability.
36.
Which statement is correct?
Spoiler extension decreases the stall speed and the minimum rate of descent, but increases the minimum descent angle
Extension of flaps causes a reduction of the stall speed, the maximum glide distance also reduces
Extension of flaps has no influence on the minimum rate of descent, as only the TAS has to be taken into account
Extension of flaps will increase (CL/CD)max, causing the minimum rate of descent to decrease.
37.
""Tuck under"" is
shaking of the control column at high Mach Number
the tendency to nose up when speed is increased into the transonic flight regime
the tendency to nose down when speed is increased into the transonic flight regime
the tendency to nose down when the control column is pulled back.
38.
The function of the stick pusher is
to pull the stick, to avoid a high speed stall
to activate and push the stick forward at or beyond a certain value of angle of attack.
to activate and push the stick forward prior to stick shaker
to vibrate the controls
39.
What is the effect of a decreasing aeroplane weight on Mcrit at n=1, when flying at constant IAS ? The value of Mcrit
is independent of the angle of attack.
remains constant
increases.
decreases.
40.
The critical Mach Number of an aeroplane can be increased by
dihedral of the wings.
vortex generators
sweep back of the wings
control deflection
41.
The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is
1.5
2.5
2.0
3.75
42.
Which type of wing arrangement decreases the static lateral stability of an aeroplane?
Increased wing span
High wing
Anhedral.
Dihedral.
43.
When the trailing edge flaps are deflected in level flight, the change in pitch moment will be
nose up
dependent on c.g. location
zero.
nose down
44.
The difference between IAS and TAS will
decrease at decreasing altitude.
increase at increasing air density
decrease at increasing speed
increase at decreasing temperature.
45.
Which of the following are used as stall warning devices?
Angle of attack indicator and speed indicator
Stick shaker and stallstrip
Angle of attack sensor and stallstrip
Stick shaker and angle of attack indicator
46.
Winglets
decrease the static lateral stability.
increase the manoeuvrability.
create an elliptical lift distribution
decrease the induced drag.
47.
For an aeroplane with one fixed value of VA the following applies. VA is
just another symbol for the rough air speed
the speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor
the maximum speed in smooth air
the speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW
48.
What is the limit load factor of a large transport aeroplane in the manoeuvring diagram?
1.5
6
2.5
3.75
49.
During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection
on the upgoing wing only
upward on the upgoing wing and downward on the downgoing wing.
downward on the upgoing wing and upward on the downgoing wing.
on the downgoing wing only
50.
On a non swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre
shifts from 25% to about 50% of the aerofoil chord
shifts aft by about 10%.
remains unchanged
slightly shifts forward
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