AERODYNAMICS

MOCK-EXAM
1. What force relationship must exist for an aircraft to maintain equilibrium in flight?
A. Lift must equal weight
B. The sum of all forces and moments acting about the center of gravity must equal zero
C. Thrust must equal weight
D. Thrust must equal drag

2. What is static pressure?

A. Mass per unit volume
B. Average molecular energy of air molecules
C. Weight of a column of air over a given area
D. Air’s resistance to flow

3. What change in atmospheric pressure occurs with an increase in altitude?

A. Static pressure increases
B. Static pressure decreases
C. No effect
D. Static pressure remain constant

4. An increase in which of the following will result in an increase in air viscosity?

A. Pressure
B. Density
C. Temperature
D. Weight

5. What are the best density conditions for producing lift?

A. Warm, high pressure, dry air
B. Warm, low pressure, moist air
C. Cold, low pressure, moist air
D. Cold, high pressure, dry air

6. According to the General Gas Law, an increase in temperature has what effect on density?
A. Density decreases
B. Density increases
C. Density remains constant
D. None of the above

7. Roll is defined as the movement of the lateral axis about which axis?
A. Lateral
B. Longitudinal
C. Vertical
D. Horizon

8. Pitch is defined as the movement of the longitudinal axis about which axis?
A. Lateral
B. Longitudinal
C. Vertical
D. Horizon

9. Yaw is defined as the movement of the longitudinal axis about which axis?
A. Lateral
B. Longitudinal
C. Vertical
D. Horizon

10. The aspect ratio (AR) is:

A. The ratio of the wingspan to the chord
B. The ratio of the root chord to the tip chord
C. The ratio of the wingspan to the average chord
D. The ratio of the wingspan to the root chord
11. According to the continuity equation for incompressible airflow, what is the relationship between
area, airflow velocity and mass airflow?
A. Airflow velocity increases as stream tube area increases, to maintain constant mass airflow
B. Airflow velocity increases as stream tube area decreases, to maintain constant mass airflow
C. Airflow velocity remains constant as stream tube area decreases, to maintain constant mass airflow
D. Airflow velocity decreases as stream tube area decreases, to maintain constant mass airflow

12. For a given altitude, what are the properties of the input provided by the static pressure port to the
pitot-static system?
A. The static pressure value will vary with changes in the aircraft true airspeed (TAS)
B. The static pressure value will vary with changes in the aircraft angle of attack (AOA)
C. The static pressure value will vary with changes in the aircraft weight
D. The static pressure value will vary with changes in atmospheric ambient static pressure and altitude

13. What must a pilot do to maintain a constant indicated airspeed (IAS) during a climb?
A. Increase true airspeed (TAS) as altitude increases
B. Decease true airspeed (TAS) as altitude increases
C. Keep true airspeed (TAS) constant as altitude increases
D. Keep ground speed (GAS) constant as altitude increases

14. When will the value of the aircraft’s indicated airspeed indicator equal the aircraft’s true airspeed?
A. When the static pressure at aircraft altitude is less than static pressure at sea level, on a standard
day
B. When the static pressure at aircraft altitude is greater than static pressure at sea level, on a standard
day
C. When the static pressure at aircraft altitude is equal to static pressure at sea level, on a standard day
D. When the air density at aircraft altitude is equal to air density at sea level, on standard day

15. What change in indicated airspeed and dynamic pressure will occur when an aircraft accelerates to
a greater true airspeed at a constant altitude?
A. Indicated airspeed will increase
B. Indicated airspeed will decrease
C. Indicated airspeed will remain constant
D. Dynamic pressure will remain constant

16. The net aerodynamic forces can be resolved into what two component forces?
A. Lift and drag
B. Weight and drag
C. Thrust and drag
D. Dynamic and static pressure

17. What must you do to remain in formation as your aircraft takes on fuel (increasing weight) from the
tanker that is maintaining a constant altitude and true airspeed?
A. Maintain a constant AOA and TAS
B. Decrease AOA and increase TAS
C. Increase AOA and maintain constant TAS
D. Increase AOA and TAS
18. What forces act on an aircraft in flight?
A. Lift, mass and thrust
B. Lift, mass and drag
C. Lift, drag, mass and weight
D. Lift, weight, thrust and drag

19. What is the definition of power?

A. The ability to do work
B. Work done per unit of time
C. Energy due to motion
D. Mass times acceleration

20. What affect does an increase in altitude have on temperature?

A. Decreases until 25000 ft and then remains constant
B. Decreases until there are no molecules of air
C. Decreases until 36000 ft and then remains constant
D. Decreases until 0 degrees is reached

21. High density altitude will:

A. Decrease the power produced by an engine and increase the thrust produced by the propeller or jet
B. Increase the power produced by an engine and increase the thrust produced by the propeller or jet
C. Decrease the power produced by an engine and decrease the thrust produced by a propeller or jet
D. Increase the power produced by an engine and decrease the thrust produced by the propeller or jet

22. All motion or changes in aircraft attitude occurs about which position?
A. Aerodynamic center
B. Center of pressure
C. Center of gravity
D. The cockpit

23. Two planes leave manila for southern city, a distance of 900 km. plane A travels at a ground speed
of 90 kph faster than the plane B. Plane A arrives in their destination 2 hours and 15 minutes ahead of
plane B. what is the ground speed of plane A?
A. 205 KPH
B. 315 KPH
C. 240 KPH
D. 287 KPH

24. When the value on the aircraft indicated airspeed (IAS) indicator equal the aircraft true airspeed
(TAS)
A. When static pressure at aircraft altitude is less than static pressure at sea level, on a standard day
B. When static pressure at aircraft altitude is greater than static pressure at aircraft sea level, on a
standard day
C. When static pressure at aircraft altitude equals static pressure at sea level, on a standard day
D. When static pressure at aircraft altitude equals density at sea level, on standard sea level

25. An aircraft is climbing at a constant 350 KIAS. What change occurs in Mach number as altitude
increases?
A. Mach number increases
B. Mach number decreases
C. Mach number remains constant
D. There is no Mach number at this speed

26. Two identical aircraft are stabilized in level flight. Aircraft 1 is maintaining mach 2 at 40,000 feet.
Aircraft 2, is maintaining mach 2 at sea level. What can be said about their respective indicated and true
airspeed?
A. Both aircraft are maintaining the same indicated air speed
B. Both aircraft are maintaining the same true airspeed
C. The aircraft flying at sea level are maintaining a greater IAS and TAS than the aircraft at 40,000 feet.
D. The aircraft flying at 40,000 feet is maintaining a greater IAS and TAS than the aircraft at sea level.

27. The speed of sound in the atmosphere

A. Varies according to the frequency of the sound.

B. Changes with a change in temperature.
C. Changes with a change in pressure.
D. None of the above
28. When the lift of an airfoil increases, the drag will
A. Decrease.
B. Also increase.
C. Increase while the lift is changing but will return to its original value.
D. None of the above

29. As the angle of attack an airfoil increases, the center of pressure will
A. Move toward the trailing edge.
B. Remain stationary because both lift and drag components increase proportionally to increased angle
of attack.
C. Move toward the leading edge.
D. None of the above

30. Wing dihedral, a rigging consideration on most airplanes of conventional design, contributes most to
stability of the airplane about its
A. Longitudinal axis.
B. Vertical axis.
C. Lateral axis.
D. Z axis

31. An airplane wing is designed to produce lift resulting from relatively

A. Positive air pressure below and above the wing's surface.
B. Negative air pressure below the wing's surface and positive air pressure above the wing's surface.
C. Positive air pressure below the wing's surface and negative air pressure above the wing's surface.
D. None of the above

32. An airplane's center of lift is usually located aft of its center of gravity
A. So that the airplane will have a tail-heavy tendency.
B. So that the airplane will have a nose-heavy tendency.
C. To improve stability about the longitudinal axis.
D. None of the above

33. What type of flap system increases the wing area and changes the wing chamber.
A. Fowler flaps.
B. Slotted flaps.
C. Split flaps.
D. None of the above.

34. The purpose of aircraft wing dihedral is to

A. Increase lateral stability.
B. Increase longitudinal stability
C. Increase lift coefficient of the wing.
D. None of the above.

35. Which atmospheric conditions will cause the true landing speed of an aircraft to be the greatest?
A. Low temperature with low humidity.
B. High temperature with low humidity.
C. High temperature with high humidity.
D. Low temperature with high humidity.

36. The purpose of aircraft wing dihedral is to

A. Increase lateral stability.
B. Increase longitudinal stability.
C. Increase lift coefficient of the wing.
D. All of the above.

37. A wing with a very high aspect ratio (in comparison with a low aspect ratio wing) will have
A. Increased drag at high angles of attack.
B. A low stall speed.
C. Poor control qualities at low airspeed.
D. All of the above.

38. An increase in the speed at which an airfoil passes through the air increases lift because
A. The increased speed of the airflow creates a greater pressure differential between the upper and
lower surfaces.
B. The increased speed of the airflow creates a lesser pressure differential between the upper and
lower surfaces.
C. The increased velocity of the relative wind increases the angle of attack.
D. All of the above.

39. The purpose of stall strips on airplane wings is to

A. Increase lift in the areas of installation.
B. Prevent stall in the areas of installation.
C. Ensure that the wing root areas stall first.
D. None of the above.

40. IHP minus BHP is

A. indicated horsepower
B. brake horsepower
C. friction horsepower
D. propeller horsepower
41. In the equation B. drag coefficient
, Cd0 is induce coeffi
Cl2 d drag cient
πAR e coeffic D.
Cd = Cd0 + ient struct
A. Profile drag C. ural
coefficient wake drag
42. Thrust required is associated with weight and velocity while Thrust Available is associated with
A. The engine
B. The design of the airplane
C. Lift and drag produced
D. Weight

43. The altitude at which the max R/C = 0 is the

A. Service ceiling
B. Landing run
C. Take-off run
D. Absolute ceiling

44. For the maneuvering performance of airplanes, it is advantageous to have the smallest r and the
smallest ω obtainable by
A. Have the highest Load factor and The lowest possible velocity
B. Have the lowest Load factor and The highest possible velocity
C. Have the highest Load factor and The highest possible velocity
D. Have the lowest Load factor and The lowest possible velocity

45. The formula

A. range of a reciprocating engine powered airplane
B. endurance of a reciprocating engine powered airplane
C. range of a jet engine powered airplane
D. endurance of a jet engine powered airplane

46. Find the temperature at 5.5 Nautical miles at standard atmosphere.

A. 232.55K
B. 221.83K
C. 216.15K
D. 198.21K

47. A horizontal pipe, 1ft in diameter, tapers gradually to 8 in. in diameter. If the flow is 500 cu ft of water
per minute, what is the difference between the pressures at the two sections?
A. 389.39

B. 441.51

C. 577.22

D. 587.22
48. Find the speed of sound on a hot day where the temperature is 100°F.
A. 474.47

B. 857.78

C. 984.12

D. 1,160.02

49. Air at standard pressure and temperature is adiabatically compressed to 50 lb per sq in gage
pressure. What is the temperature?
A. 792.59°R
B. 793.59°R
C. 794.59°R
D. 795.59°R

50. Find the Reynold’s Number for an airplane wing 4ft chord, moving at 130mph through standard
atmosphere.
A. 4,750,932.14
B. 4,850,932.14
C. 4,950,932.14
D. 4,952,932.14