1. [Multiple Choice]
Just above the critical Mach number the first evidence of a shock
wave will appear at the (2Pt)
A. lower side of the wing.
B. leading edge of the wing.
C. trailing edge of the wing.
D. upper side of the wing.
Question analysis: No analysis
3. [Multiple Choice]
The location of the center of pressure of a positive cambered wing
at increasing angle of attack will (2Pt)
A. Shift aft
B. Not shift
C. Shift forward
D. Shift in spanwise direction
5. [Multiple Choice]
What is the relationship of the length of a curved path, r, with
tangential velocity, v, when the strength of circulation is constant as we move outwards
from the core? (2Pt)
A. Directly Proportional
B. Inversely Proportional
C. Not related
D. Constant
7. [Multiple Choice]
The lift coefficient of an aircraft in steady horizontal flight is 0.4.
Increase of angle of attack of 1 degree will increase the CL by 0.09. A vertical up gust
instantly changes the angle of attack by 5 degrees. The load factor will be (2Pt)
A. 1.09
B. 2
C. 3.19
D. 2.13
Question analysis: No analysis
8. [Multiple Choice] Given the ratio of dynamic pressure and static pressure to be 0.135,
calculate the Mach number. Assume air is the medium. (2Pt)
A. 0.539
B. 0.439
C. 0.639
D. 0.339
9. [Multiple Choice]
Stu Answer
D
Right Answer
D
Candidate’s
Score
2/2Pt
In a two-dimensional flow pattern, where the streamlines converge
the static pressure will _____. (2Pt)
A. not change
B. increase
C. increase initially, then decrease
D. decrease
Question analysis: No analysis
10. [Multiple Choice]
Stu Answer
D
Right Answer
D
Candidate’s
Score
2/2Pt
Which among the statements about Density Altitude is incorrect?
(2Pt)
A. Density altitude is found by correcting pressure altitude for temperature and humidity deviations from
the standard atmosphere
B. A high density altitude requires a higher true airspeed for takeoff and landing and will therefore
increase takeoff and landing distances
C. A high density altitude will decrease the power produced by an engine because less oxygen is available
for combustion
D. None, all statements above are correct
Question analysis: No analysis
11. [Multiple Choice]
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
An aircraft model is placed in a certain wind tunnel airstream. The
density of the airstream decreases to half of the original value. The aerodynamic drag
will decrease with a factor (2Pt)
A. 1.4
B. 4
C. 2
D. 8
Question analysis: No analysis
12. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
Shock stall is (2Pt)
A. separation of the flow at the trailing edge of the wing at high Mach Numbers.
B. separation of the boundary layer behind the shock wave.
C. separation of the flow at high angles of attack and at high Mach Numbers.
D. separation of the flow behind the bow wave.
Question analysis: No analysis
13. [Multiple Choice] An aircraft is cruising at FL110. What is the ambient temperature
(K)? (2Pt)
A. 266.37
B. 479.46
C. 390.06
D. 557.92
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
Question analysis: No analysis
14. [Multiple Choice]
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
Given g = 10m/s^2, an aircraft is in a steady turn, at a constant
TAS of 300kt, and a bank angle of 45 degrees. Its turning radius is (2Pt)
A. None of the above
B. 3254 m
C. 2381 m
D. 4876 m
Question analysis: No analysis
15. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
On five-digit NACA airfoil, the third digit corresponds to the
camber. What does it mean if the third digit is 1. (2Pt)
A. Critical
B. Reflex
C. Turbulent
D. Simple
Question analysis: No analysis
16. [Multiple Choice] An aircraft has a mass of 7200 kg and a wing span of 12 m. If the
wing loading is 1.968 kN/m^2, what is the induced drag when flying at speeds of 200
knots at sea-level? (2Pt)
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
A. 1500 N
B. 1700 N
C. 1800 N
D. 1600 N
Question analysis: No analysis
17. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
The aircraft total drag in straight and level flight is lowest when
the (2Pt)
A. Induced drag is lowest
B. Parasite drag is equal to the induced drag
C. Parasite drag equals twice the induced drag
D. Induced drag is equal to zero
Question analysis: No analysis
18. [Multiple Choice]
Stu Answer
D
Right Answer
D
Candidate’s
Score
A 5000 lb airplane with wing area of 250 sq ft and power available
of 450 hp is at flight sea level standard condition. The airplane drag to lift relation is
close to CD = 0.025 + 0.048 CL^2. At flight speed of 180 mph, the airplane drag
coefficient is _______. (2Pt)
A. 0.0195
B. 0.0206
C. 0.0237
D. 0.0278
2/2Pt
Question analysis: No analysis
20. [Multiple Choice]
Stu Answer
D
Right Answer
D
Candidate’s
Score
2/2Pt
Which among the following statements about symmetrical and
unsymmetrical airfoils is incorrect? (2Pt)
A. An unsymmetrical airfoil is able to produce an uneven pressure distribution even at zero AOA.
B. A symmetric airfoil at zero angle of attack produces identical velocity increases and static pressure
decreases on both the upper and lower surfaces.
C. The first two digits of a 4-digit airfoil will give information whether an airfoil is unsymmetrical or not.
D. Because of positive camber, the area in the streamtube above the wing is larger than area in the
streamtube below the wing and the airflow velocity above the wing is greater than the velocity below
the wing.
Question analysis: No analysis
21. [Multiple Choice]
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
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 ______. (2Pt)
A. 1.4
B. 8
C. 2
D. 4
Question analysis: No analysis
22. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
When the Mach number is slowly increased in straight and level
flight the first shockwaves will occur (2Pt)
A. on the underside of the wing.
B. at the wing root segment, upperside.
C. somewhere on the fin.
D. somewhere on the hoizontal tail.
Question analysis: No analysis
23. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
A stealth jet is flying at an altitude of 20km at a velocity of 2500
miles/hr. what is the mach angle. (2Pt)
A. 6.43 deg
B. 15.30 deg
C. 18.20 deg
D. 12.40 deg
Question analysis: No analysis
24. [Multiple Choice] It is the point in a fluid stream where the diameter of the stream
is the least and fluid velocity is at its maximum. (2Pt)
A. Converging-Diverging
B. Stagnation
C. Walls
D. Vena Contracta
Stu Answer
D
Right Answer
D
Candidate’s
Score
2/2Pt
Question analysis: No analysis
25. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
What is the type of flow if the computed Reynolds number
exceeds 4,000? (2Pt)
A. Laminar
B. Turbulent
C. Transient
D. Uniform
Question analysis: No analysis
26. [Multiple Choice]
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
A plain flap will increase CLmax by (2Pt)
A. Increasing the camber of the airfoil
B. Increasing angle of attack
C. Boundary layer control
D. Center of lift movement
Question analysis: No analysis
27. [Multiple Choice] To increase the critical Mach number a conventional aerofoil
should ______. (2Pt)
A. have a large camber
B. have a large leading edge radius
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
C. have a low thickness to chord ratio
D. be used with a high angle of attack
Question analysis: No analysis
28. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
In supersonic flight aerofoil pressure distribution is (2Pt)
A. triangular.
B. rectangular.
C. the same as in subsonic flight.
D. irregular.
Question analysis: No analysis
29. [Multiple Choice]
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
If a symmetrical aerofoil is accelerated from subsonic to
supersonic speed the centre of lift will move _____. (2Pt)
A. aft to the trailing edge
B. forward to the leading edge
C. aft to the mid chord
D. forward to the mid chord
Question analysis: No analysis
30. [Multiple Choice]
Stu Answer
D
Right Answer
D
Candidate’s
Score
2/2Pt
A body is placed in a certain airstream. The airstream velocity
increases by a factor 4. The aerodynamic drag will increase with a factor ______. (2Pt)
A. 8
B. 4
C. 12
D. 16
Question analysis: No analysis
32. [Multiple Choice]
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
How will the density and temperature change in a supersonic flow
from a position in front of a shock wave to behind it? (2Pt)
A. Density will increase, temperature will increase.
B. Density will decrease, temperature will decrease.
C. Density will increase, temperature will decrease.
D. Density will decrease, temperature will increase.
Question analysis: No analysis
34. [Multiple Choice] What is the induced drag at 100 knots of a monoplane of mass
2400 kg having a wing span of 16 m? (2Pt)
A. 632.6 lbf
B. 425.9 N
C. 632.8 N
D. 425.9 lbf
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
Question analysis: No analysis
35. [Multiple Choice]
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
When the air has passed through a normal shock wave the Mach
number is (2Pt)
A. equal to
B. lower than before but still greater than
C. less than 1.
D. higher than before.
Question analysis: No analysis
36. [Multiple Choice]
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
An aircraft has a stall speed of 100kt at a load factor n=1. In a
turn with a load factor of n=2, the stall speed is (2Pt)
A. 141 kt
B. 282 kt
C. 200 kt
D. 70 kt
Question analysis: No analysis
37. [Multiple Choice] 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 ______.
(2Pt)
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
A. the top to beneath the wing via the leading edge
B. beneath to the top of the wing via the wing tip
C. beneath to the top of the wing via the trailing edge
D. the top to beneath the wing via the wing’s trailing edge
Question analysis: No analysis
40. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
The Mach number _____. (2Pt)
A. is the ratio between the TAS of the aeroplane and the sea level speed of sound
B. increases as the local speed of sound decreases
C. increases at a given TAS, when the temperature rises
D. is the ratio between the IAS of the aeroplane and the local speed of sound
Question analysis: No analysis
41. [Multiple Choice]
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
This gas law states that pressure and volume are inversely related
when the temperature is constant. (2Pt)
A. Boyle’s
B. Avogadro’s
C. Boltzmann’s
D. Charles
Question analysis: No analysis
42. [Multiple Choice]
Stu Answer
C
Right Answer
C
Candidate’s
Score
2/2Pt
By what percent does the lift increase in a steady level turn at 45
degrees angle of bank, compared to straight and level flight? (2Pt)
A. 0.52
B. 0.19
C. 0.41
D. 0.31
Question analysis: No analysis
44. [Multiple Choice]
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
What force is required to push a flat plate, 3 in by 2 in at a speed
of 35 fps in a direction perpendicular to its surface? (2Pt)
A. 0.078 lbs
B. 22.36 lbs
C. 11.18 lbs
D. 1.55 lbs
Question analysis: No analysis
45. [Multiple Choice] The flight Mach number is 0.8 and the TAS is 400 kts. What is the
speed of sound? (2Pt)
A. 500 kts
B. 600 kts
C. 320 kts
D. 480 kts
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
Question analysis: No analysis
47. [Multiple Choice]
Stu Answer
A
Right Answer
A
Candidate’s
Score
2/2Pt
An aeroplane has a stall speed of 78 KCAS at its gross weight of
6,850 lbs. What is the stall speed when the weight is 5,000 lbs? (2Pt)
A. 67 KCAS
B. 91 KCAS
C. 57 KCAS
D. 78 KCAS
Question analysis: No analysis
48. [Multiple Choice]
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
What is the CLmax of an aircraft with a wing loading of 700
Newtons per square meter and stalling velocity of 115 miles per hour? Assumes
standard sea level conditions. (2Pt)
A. 0.465
B. 0.433
C. 0.233
D. 0.216
Question analysis: No analysis
49. [Multiple Choice] What is μ (slugs/ft-s) at the an altitude where the speed of sound
equals 692.662 mph? (2Pt)
Stu Answer
B
Right Answer
B
Candidate’s
Score
2/2Pt
A. 3.64 x 10^-7
B. 3.24 x 10^-7
C. 3.04 x 10^-7
D. 3.84 x 10^-7