T 2026 Aerodynamics Final Mock Exam

1. In a supersonic airstream, which of the following flow properties are increased as the fluid flows across an expansion wave?

A. velocity and mach number

B. pressure and mach number

C. velocity and mass density

D. pressure and mass density

A. velocity and mach number

2. Which of the following factors will lead to an increase of ground distance during a glide, while maintaining the appropriate minimum glide angle speed?

A. Tailwind

B. Increase of aircraft mass.

C. Decrease of aircraft mass.

D. Headwind

A. Tailwind

3. What is the true velocity of the U2 Dragon Lady flying at Mach 2.5 if it is at its cruise altitude of 24 km.

A. 1132 m/s

B. 845 m/s

C. 790 m/s

D. 737 m/s

D. 737 m/s

4. The best rate of climb at a constant gross mass *

A. decreases with increasing altitude since the thrust available decreases due to the lower air density.

B. increases with increasing altitude due to the higher true airspeed.

C. is independent of altitude.

D. increases with increasing altitude since the drag decreases due to the lower air density.

A. decreases with increasing altitude since the thrust available decreases due to the lower air density.

5. In a supersonic airstream, which of the following flow properties are increased as the fluid flows across a compression wave?

A. mach number, mass density, velocity

B. pressure, mass density, mach number

C. velocity, mass density, temperature

D. mass density, pressure, temperature

D. mass density, pressure, temperature

6. Drooping of helicopter blades is compensated by. *

A. centrifugal force,

B. dragging.

C. leading.

D. flapping.

A. centrifugal force,

7. Moving the center of gravity from the forward to the aft limit (gross mass, altitude and airspeed remain unchanged)

A. decreases the induced drag and reduces the power required.

B. increases the power required.

C. affects neither drag nor power required.

D. increases the induced drag.

A. decreases the induced drag and reduces the power required.

8. As the flow passes through a normal shockwave *

A. Mach number increases

B. Mach number decreases to a value just above Mach 1

C. Density decreases

D. Pressure increases

D. Pressure increases

9. 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 :

A. Higher critical Mach number

B. Increased longitudinal stability

C. Greater strength

D. Lower stalling speed

A. Higher critical Mach number

10. An aircraft with a wing loading of 50psf is in a level flight at a velocity of 150fps. What is the induced drag. Assume standard sea level conditions. AR=6

A. 0.014

B. 0.21

C. 0.221

D. 0.185

D. 0.185

11. An aircraft uses a NACA 23015 airfoil. Where is the location of its maximum camber given the following dimensions:

A. 1.47 ft from LE

B. 0.74 ft from TE

C. 1.47 ft from TE

D. 0.74 ft from LE

D. 0.74 ft from LE

12. An airplane will perform a turn with a 120 meter radius and a velocity of 53 meters per second will require and angle of bank of

A. 58 deg

B. 67 deg

C. 47 deg

D. 53 deg

B. 67 deg

13. With the centre of gravity on the forward limit which of the following is to be expected?

A. A decrease in the landing speed.

B. A decrease of the stalling speed.

C. A decrease in range.

D. A tendency to yaw to the right on take-off.

C. A decrease in range.

14. At sea level, an airplane rate of climb is 1,000 feet per minute. Its absolute ceiling is 16,500 feet. What is the rate of climb at 12,345 feet altitude?

A. 294 fpm

B. 283 fpm

C. 251 fpm

D. 266 fpm

C. 251 fpm

15. A heavy and light aircraft is both flown at a maximum lift to drag ratio of 12. Assuming all things equal,

A. The heavier aircraft will have the longer gliding distance than the lighter aircraft.

B. The heavier aircraft will not have the same gliding distance with the lighter aircraft depending on the headwind/tailwind.

C. The heavier aircraft will have the shorter gliding distance than the lighter aircraft.

D. The heavier aircraft will have the same gliding distance with the lighter aircraft.

D. The heavier aircraft will have the same gliding distance with the lighter aircraft.

16. A circular pipe with an initial diameter of 1 meter gradually tapers to 0.6 meters in diameter as it runs for 20 meters. Initially, water enters at a speed of 40 meters per second. What is the rate of change in velocity?

A. 1.28 meters per second per meter run

B. - 1.82 meters per second per meter run

C. 1.82 meters per second per meter run

D. - 1.28 meters per second per meter run

A. 1.28 meters per second per meter run

17. Given is an airplane wing with a rectangular planform, an aspect ratio of 5, a span of 10 meters, and a NACA 23015 airfoil section. Solve for a. wing area (sqm) b. maximum thickness (cm) of the chord

A. a. 20, b. 0.30

B. a. 20, b. 30

C. a. 20, b. 15

D. a. 20, b. 0.15

B. a. 20, b. 30

18. The airplane drag coefficient Cd is conveniently expressed as function of the lift coefficient Cl in the form Cd = CDo + ( Cl^2 / (pi e AR) ). At minimum power required, the airplane drag coefficient Cd is replated to the parasite drag coefficient by the equation

A. Cd = CDo

B. Cd = 2 CDo

C. Cd = 4 CDo

D. Cd = 3 CDo

C. Cd = 4 CDo

19. For a symmetrical airfoil drag coefficient at zero lift is 0.025 and induced drag coefficient is 0.0025. Find the total drag coefficient.

A. 0.0275

B. 0.0525

C. 0.05

D. 0.1

A. 0.0275

20. As a general rule, if the aerodynamic angle of incidence (angle of attack) of an aerofoil is slightly increased, the centre of pressure will.

A. move forward towards the leading edge.

B. move rearwards towards the trailing edge.

C. never move.

D. move from the upper surface towards the bottom surface

A. move forward towards the leading edge.

21. An aircraft uses a NACA 23015 airfoil, this means that the maximum camber is located at a distance of ____% of the chord from the leading edge

A. 15

B. 2

C. 30

D. 23

A. 15

22. As airflow passes through a normal shock wave, which of the following changes in static pressure (i), density (ii), and Mach number (iii) will occur?

A. (i) increase; (ii) decrease; (iii) < 1.0

B. (i) increase; (ii) increase; (iii) < 1.0

C. (i) decrease; (ii) increase; (iii) < 1.0

D. (i) increase; (ii) decrease; (iii) > 1.0 or < 1.0

B. (i) increase; (ii) increase; (iii) < 1.0

23. The velocity and temperature in front of a normal shock wave are 685 m/s and 500 K, respectively. What is the Mach number behind the shock? (k = 1.4, R = 287.08 J/kg.K)

A. 0.91

B. 0.69

C. 0.88

D. 0.58

B. 0.69

24. What is the drag coefficient experienced by a flat plate with an angle of attack of 3 degrees when inside a test section with Mach 2.8 flow?

A. 0.08

B. 0.004

C. 0.008

D. 0.04

B. 0.004

25. A high aspect ratio wing. *

A. has less induced drag than a low aspect ratio wing.

B. is stiffer than a low aspect ratio wing.

C. has a higher stall angle than a low aspect ratio wing.

D. is used by fighter jets for maneuverability.

A. has less induced drag than a low aspect ratio wing.

26. A propeller aircraft with the aspect ratio of 6 is flying at maximum range settings. What is zero lift drag coefficient if the Cl is 0.75?

A. 0.0448

B. 0.0895

C. 0.0298

D. 0.0099

C. 0.0298

27. The positive maneuvering load factor for normal category should not be greater than

A. 3.8

B. 4.4

C. 6

D. 2.1

A. 3.8

28. An airplane is making a 40 deg. banked turn of 565 ft radius. What should be the airspeed? (mph)

A. 80.3

B. 83.2

C. 81.9

D. 84.2

D. 84.2

29. Air passes a normal shock wave. Which of the following statements is correct?

A. The temperature increases.

B. The temperature decreases.

C. The pressure decreases.

D. The velocity increases.

A. The temperature increases.

30. Airplane is making a turn of 200 ft radius at a speed of 190 mph. What is the load factor?

A. 11.2

B. 8.9

C. 12.1

D. 9.2

C. 12.1

31. Plane is cruising at 9000 meters. If the pitot tube measures 35 kPa, what is the true airspeed of the airplane? (m/s)

A. 135

B. 165

C. 145

D. 155

A. 135

32. An aircraft whose landing speed is 38 miles per hour goes into a vertically banked turn of minimum radius at 80 miles per hour. What is the minimum radius?

A. 96.5 ft

B. 119.5 ft

C. 122.2 ft

D. 202.7 ft

A. 96.5 ft

33. How does the lift coefficient for maximum range vary with altitude? (No compressibility effects.)

A. Only at low speeds the lift coefficient decreases with increasing altitude.

B. The lift coefficient decreases with increasing altitude.

C. The lift coefficient increases with increasing altitude.

D. The lift coefficient is independant of altitude.

D. The lift coefficient is independant of altitude.

34. A jet aircraft with the aspect ratio of 6 is flying at maximum range settings. What is zero lift drag coefficient if the Cl is 0.75?

A. 0.0895

B. 0.0099

C. 0.0448

D. 0.0298

A. 0.0895

35. An aircraft is flying at an air mass 1,000 feet above sea level on a standard atmosphere. What is the absolute viscosity coefficient at this point?

A. 0.00373 slug / ft sec

B. 0.000000373 slug / ft sec

C. 0.000373 slug / ft sec

D. 0.0000373 slug / ft sec

B. 0.000000373 slug / ft sec

36. The drag polar equation is given by: CD = 0.0358 + 0.046CL^2

A. 0.743

B. 0.0358

C. 0.0716

D. 0.882

D. 0.882

37. Emirates EK334 flight must roll to the right to get to waypoint TARA. During this, (disregard rudder movement for coordinated turns)

A. the right wing aileron is pointed downwards, the left wing aileron is pointed upwards.

B. the right wing aileron is pointed upwards, the left wing aileron is pointed downwards.

C. the right wing aileron is pointed downwards, the left wing aileron is also pointed downwards.

D. the right wing aileron is pointed upwards, the left wing aileron is also pointed upwards.

B. the right wing aileron is pointed upwards, the left wing aileron is pointed downwards.

38. This is the Mach number at which the aerodynamic drag begins to increase rapidly.

A. Critical Mach Number

B. Mach 1

C. Supercritical point

D. Drag divergence Mach number

D. Drag divergence Mach number

39. 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:

A. 141 kt

B. 150 kt

C. 122 kt

D. 82 kt

C. 122 kt

40. For an aircraft climbing at a constant IAS the Mach number will *

A. remain constant

B. initially show an increase, then decrease

C. increase

D. decrease

C. increase

41. The drag polar equation of the propeller driven is given by: CD = 0.025 + 0.062CL^2

A. 0.1

B. 0.075

C. 0.033

D. 0.05

A. 0.1

42. On a helicopter, what is blade dragging?

A. Movement of each blade vertically about their lateral hinges.

B. Movement of each blade horizontally about their vertical hinge

C. Rotation of the blade around the main rotor mast.

D. Contact of the blade tips on the ground.

B. Movement of each blade horizontally about their vertical hinge

43. An airplane is flying at 10,000ft altitude. The difference between impact and static pressure is 0.25 lb per sq in. What is the airspeed in knots?

A. 130 kt

B. 120 kt

C. 100 kt

D. 110 kt

B. 120 kt

44. If the CG is located at 30% of MAC and the LEMAC is at station 1010, in what station would you find the CG if the MAC is 100 inches?

A. St. 1010

B. St. 1110

C. St. 980

D. St. 1040

D. St. 1040

45. For a given IAS an increase in altitude will result in.

A. an increase in induced drag.

B. no change in the value of induced drag.

C. a decrease in profile drag.

D. an increase in profile drag.

A. an increase in induced drag.

46. Consider an airfoil in a flow at standard sea level conditions w/ the free stream velocity of 50 m/s. At the given point on airfoil the pressure is 90000Pa, calculate the velocity at this point.

A. 124

B. 154

C. 145

D. 134

C. 145

47. Two methods to increase the critical Mach Number are: *

A. positive cambering of the aerofoil and sweep back of the wing.

B. thin aerofoils and sweep back of the wing.

C. thick aerofoils and dihedral of the wing.

D. thin aerofoils and dihedral of the wing.

B. thin aerofoils and sweep back of the wing.

48. Which of the following statements about static lateral and directional stability is correct?

A. The effects of static lateral and static directional stability are completely independent of each other because they take place about different axis.

B. An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to spiral dive. (spiral instability)

C. An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to "Dutch roll".

D. Static directional stability can be increased by installing more powerful engines.

B. An aeroplane with an excessive static directional stability in relation to its static lateral stability, will be prone to spiral dive. (spiral instability)

49. What is the critical velocity of an airplane during its cruise at 15,000 ft, flying at a speed of 400 kts.

A. 306 ft/s

B. 675 ft/s

C. 1032 m/s

D. 1003 ft/s

D. 1003 ft/s

50. Rate of descent can be minimized when the *

A. parasite drag equals three times the induced drag

B. parasite drag equals one-third of induced drag

C. parasite drag equals the induced drag

D. parasite drag is greater than the induced drag

B. parasite drag equals one-third of induced drag