Email
info@vayudootaviation.com
Phone No
+91 7276526726
become a pilot
Home
About us
courses
CPL
ATPL
RTR(A)
Airline Cadet Program
IGRUA Entrance Prep
B.Sc. Aviation
Pilot Training
INDIA
USA
CANADA
SOUTH AFRICA
NEW ZEALAND
EUROPE
Aircraft Type-Rating
Airbus A320
Boeing 737
Blogs
contact
CPL Test Series
Question Bank
Questions for INDIGO AERODYNAMIC 5259-5689
Answer the following questions
Test Mode
Training Mode
1.
How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight?
Decreasing
Decreasing, then increasing
Increasing, then decreasing.
Increasing
2.
Which kind of boundary layer has the strongest change in velocity close to the surface?
Turbulent boundary layer
Laminar boundary layer
Transition boundary layer
No difference
3.
The location of the centre of pressure of a positive cambered wing at increasing angle of attack will
shift in spanwise direction.
shift forward
shift aft.
not shift.
4.
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
150 kt.
82 kt.
141 kt
122 kt.
5.
When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of
Greater strength
Increased longitudinal stability
Lower stalling speed
Higher critical Mach number
6.
Which of the following are used as stall warning devices?
Stick shaker and angle of attack indicator
Angle of attack indicator and speed indicator
Stick shaker and stallstrip
Angle of attack sensor and stallstrip
7.
Air passes a normal shock wave. Which of the following statements is correct?
The temperature increases
The temperature decreases
The velocity increases
The pressure decreases
8.
The induced angle of attack is the result of
a large local angle of attack in a two dimensional flow.
downwash due to flow separation
downwash due to tip vortices.
change in direction of flow due to the effective angle of attack.
9.
When the C.G. position is moved forward, the elevator deflection for a manoeuvre with a load factor greater than 1 will be
unchanged
dependent on trim position
larger.
smaller.
10.
Vortex generators on the upper side of the wing
decrease wave drag.
increase wave drag
decrease critical Mach Number.
increase critical Mach Number
11.
Deploying a Fowler flap, the flap will
just move aft
just turn down
move aft, then turn down
turn down, then move aft.
12.
When the Mach number is slowly increased in straight and level flight the first shockwaves will occur
on the underside of the wing
somewhere on the fin
somewhere on the hoizontal tail.
at the wing root segment, upperside
13.
The effect of a positive wing sweep on static directional stability is as follows
Negative dihedral effect
Stabilizing effect
Destabilizing dihedral effect
No effect
14.
The vane of a stall warning system with a flapper switch is activated by the change of the
centre of gravity
centre of pressure.
point of lowest pressure.
stagnation point
15.
Which statement about the trim position is true related to centre of gravity and adjustable stabiliser position ?
A nose heavy aeroplane requires that the stabiliser leading edge is lower than compared with a tail heavy aeroplane
At the forward limit for centre of gravity, stabiliser trim is adjusted maximum Nose Down to obtain maximum elevator authority at take off rotation
Because characteristic speeds at take off do not vary with centre of gravity location, the need for stabiliser adjustment is dependent on flap position only.
A nose heavy aeroplane requires that the stabiliser leading edge is higher than compared with a tail heavy aeroplane
16.
Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
Tapered.
Elliptical.
Rectangular.
Circular.
17.
Dihedral of the wing is
the angle between the 0.25 chord line of the wing and the vertical axis.
the angle between the 0.25 chord line of the wing and the lateral axis.
the angle between the 0.25 chord line of the wing and the horizon
the angle between the leading edge of the wing and the lateral axis
18.
Which load factor determines VA?
manoeuvring flap limit load factor
manoeuvring ultimate load factor
manoeuvring limit load factor
gust load factor at 66 ft/sec gust
19.
The buffet margin
is always positive at Mach numbers below MMO.
decreases during a descent with a constant Mach number.
increases during a descent with a constant IAS.
is always greatest after a stepclimb has been executed
20.
The loss of total pressure in a shock wave is due to the fact that
the friction in the boundary layer is higher.
the speed reduction is too high.
kinetic energy in the flow is changed into heat energy.
the static pressure decrease is comparatively high.
21.
What wing shape or wing characteristic is the least sensitive to turbulence
wing dihedral
winglets
straight wings
swept wings
22.
Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
fit the engine intakes better to the fuselage
apply area rule.
increase the strength of the wing root junction.
improve the low speed characteristics
23.
The shape of the gust load diagram is also determinated by the following three vertical speed in ft/s (clean configuration)
25, 50, 66
25, 55, 75
15, 56, 65
35, 55, 66
24.
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.
150 N.
225 N.
375 N.
25.
From the polar diagram of the entire aeroplane one can read
the minimum drag and the maximum lift.
the maximum CL/CD ratio and maximum lift coefficient
the minimum drag coefficient and the maximum lift.
the minimum CL/CD ratio and the minimum drag.
26.
Which statement about a primary control surface controlled by a servo tab, is correct ?
Due to the effectiveness of the servo tab the control surface area can be smaller
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
27.
Dihedral of the wing
is the only way to increase the static lateral stability
is only positive for aeroplanes with high mounted wings.
decreases the static lateral stability.
increases the static lateral stability
28.
When flutter damping of control surfaces is obtained by mass balancing, these weights will be located with respect to the hinge of the control surface
in front of the hinge
above the hinge.
below the hinge
behind the hinge
29.
What is the approximate value of the lift of an aeroplane at a gross weight of 50 000 N, in a horizontal coordinated 45 degrees banked turn ?
70 000 N
60 000 N
50 000 N
80 000 N
30.
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
77%.
169%.
59%.
130%.
31.
During landing of a low-winged jet aeroplane, the maximum elevator up deflection is normally required when the flaps are
up and the C.G. is fully forward
fully down and the C.G. is fully forward.
up and the C.G. is fully aft.
fully down and the C.G. is fully aft.
32.
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
increase and the rate of descent will decrease
decrease and the rate of descent will increase
increase and the rate of descent will increase
decrease and the rate of descent will decrease
33.
Which statement with respect to the climb is correct ?
At constant TAS the Mach number decreases
At constant Mach number the IAS increases
At constant IAS the Mach number increases
At constant IAS the TAS decreases
34.
Mcrit is the free stream Mach Number at which
somewhere about the airframe Mach 1 is reached locally
the critical angle of attack is reached
Mach buffet occurs.
shockstall occurs
35.
How does stalling speed (IAS) vary with altitude?
It increases with increasing altitude, because the density decreases.
It remains constant at lower altitudes but increases at higher altitudes due to compressibility effects
It remains constant at lower altitudes but decreases at higher altitudes due to compressibility effects.
It remains constant
36.
The trailing edge flaps when extended
increase the zero lift angle of attack
worsen the best angle of glide
significantly increase the angle of attack for maximum lift
significantly lower the drag
37.
Which of the following statements about boundary layers is correct?
The turbulent boundary layer gives a lower skin friction than the laminar boundary layer
The turbulent boundary layer will separate more easily than the laminar boundary layer
The turbulent boundary layer has more kinetic energy than the laminar boundary laye
The turbulent boundary layer is thinner than the laminar boundary layer.
38.
Which moments or motions interact in a dutch roll?
Pitching and rolling
Pitching and adverse yaw.
Pitching and yawing
Rolling and yawing
39.
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 the lift/drag ratio, which changes with angle of attack
The wind and weight together with power loading, which is the ratio of power output to the weight
The wind and CLmax
40.
""Tuck under"" is
the tendency to nose down when the control column is pulled back.
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
41.
What will increase the sensitivity to Dutch Roll?
An increased anhedral
An increased static lateral stability.
A forward movement of the centre of gravity.
An increased static directional stability
42.
In what way do (1) induced drag and (2) parasite drag alter with increasing speed?
(1) increases and (2) decreases.
(1) increases and (2) increases
(1) decreases and (2) increases
(1) decreases and (2) decreases.
43.
""Flutter"" may be caused by
roll control reversal
low airspeed aerodynamic wing stall.
high airspeed aerodynamic wing stall
distorsion by bending and torsion of the structure causing increasing vibration in the resonance frequency
44.
When air has passed through a shock wave the speed of sound is
decreased.
increased.
decreased and beyond a certain Mach number start increasing again
not affected
45.
If the total sum of moments about one of its axis is not zero, an aeroplane
would experience an angular acceleration about that axis
would not be affected because the situation is normal
would fly a path with a constant curvature
would be difficult to control
46.
Which of the following statements is correct ?I When the critical engine fails during take-off the speed VMCL can be limiting.II The speed VMCL is always limited by maximum rudder deflection
I is correct, II is correct
I is incorrect, II is incorrect
I is correct, II is incorrect
I is incorrect, II is correct
47.
One of the requirements for dynamic stability is
effective elevator
a large deflection range of the stabilizer trim
positive static stability
a small C.G. range
48.
High Aspect Ratio, as compared with low Aspect Ratio, has the effect of
Increasing induced drag and decreasing critical angle of attack
Increasing lift and drag
Increasing lift and critical angle of attack
Decreasing induced drag and critical angle of attack
49.
When the air is passing through a shock wave the density will
increase.
decrease.
stay constant
decrease and beyond a certain Mach number start increasing again
50.
In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack will
increase.
decrease.
increase or decrease depending on type of flap.
remain constant.
Submit
Make New Set