# Fundamental Aerodynamics Test 1

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]

D 

D

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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]

D 

D

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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]

C 

C

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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]

B 

B

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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

A 

A

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Question analysis: No analysis

14. [Multiple Choice]

C 

C

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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]

B 

B

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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)

B 

B

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A. 1500 N

B. 1700 N

C. 1800 N

D. 1600 N

Question analysis: No analysis

17. [Multiple Choice]

B 

B

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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]

D 

D

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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]

D 

D

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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]

C 

C

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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]

B 

B

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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]

B 

B

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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

D 

D

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Question analysis: No analysis

25. [Multiple Choice]

B 

B

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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]

A 

A

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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

C 

C

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C. have a low thickness to chord ratio

D. be used with a high angle of attack

Question analysis: No analysis

28. [Multiple Choice]

B 

B

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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]

C 

C

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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]

D 

D

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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]

A 

A

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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

B 

B

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Question analysis: No analysis

35. [Multiple Choice]

C 

C

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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]

A 

A

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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)

B 

B

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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]

B 

B

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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]

A 

A

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This gas law states that pressure and volume are inversely related

when the temperature is constant. (2Pt)

A. Boyle’s

C. Boltzmann’s

D. Charles

Question analysis: No analysis

42. [Multiple Choice]

C 

C

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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]

A 

A

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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

A 

A

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Question analysis: No analysis

47. [Multiple Choice]

A 

A

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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]

B 

B

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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)

B 

B

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A. 3.64 x 10^-7

B. 3.24 x 10^-7

C. 3.04 x 10^-7

D. 3.84 x 10^-7