Airplanes and Aerodynamics

Question 1

What is one purpose of wing flaps

a. enable the pilot to make steeper approaches to a landing without increasing airspeed.
b. relieve the pilot of maintaining continuous pressure on the controls.
c. to decrease wing area to vary the lift

Answer 1

a. enable the pilot to make steeper approaches to a landing without increasing airspeed

Question 2

One main function of flaps during approach and landing:

a. decrease angle of descent without increasing airspeed.
b. permit touchdown at a higher indicated airspeed.
c. increase angle of descent without increasing airspeed.

Answer 2

c. increase angle of descent without increasing airspeed.

Question 3

What is the purpose of the rudder on an airplane?

a. to control yaw
b. to control overbanking tendency
c. to control roll

Answer 3

a. to control yaw

Question 4

Which is not a primary flight control:

a. Flaps
b. Stabilator
c. Ailerons

Answer 4

a. Flaps.

Question 5

The elevator controls which movement axis?

a. Longitudinal
b. Lateral
c. Vertical

Answer 5

b. Lateral

Question 6

Which statement is true:

a. Effectiveness of each control surface increases with speed because there is more airflow over them.
b. Only when all three primary flight controls move in sequence do the airflow and pressure distribution change over and around the airfoil.
c. Primary flight controls include ailerons, rudder, elevator, and trim systems.

Answer 6

a. Effectiveness of each control surface increases with speed because there is more airflow over them.

Question 7

Which of the following is true about flaps?

a. Flaps are attached to the leading edge of the wing and are used to increase wing lift.
b. Flaps allow an increase in the angle of descent without increasing airspeed.
c. Flaps are high drag devices deployed from the wings to reduce lift.

Answer 7

b. Flaps allow an increase in the angle of descent without increasing airspeed.

Question 8

Which device is a secondary flight control?

a. Spoilers
b. Ailerons
c. Stabiliators

Answer 8

a. Spoilers

Question 9

Trim systems are designed to do what?

a. They relieve the pilot of the need to maintain constant pressure on the flight controls.
b. They are used during approach and landing to increase wing lift.
c. They move in the opposite direction from one another to control roll.

Answer 9

a. They relieve the pilot of the need to maintain constant pressure on the flight controls.

Question 10

The four forces acting on an airplane in flight are:

a. lift, weight, thrust, and drag.
b. lift, weight, gravity, and thrust.
c. lift, gravity, power, and friction.

Answer 10

a. lift, weight, thrust, and drag.

Question 11

When are the four forces that act on an airplane in equilibrium?

a. During unaccelerated level flight
b. When the aircraft is accelerating
c. When the aircraft is at rest on the ground

Answer 11

a. During unaccelerated level flight

Question 12

What is the relationship of lift, drag, thrust, and weight when the airplane is in straight and level flight?

a. Lift equals weight and thrust equals drag
b. Lift, drag, and weight equal thrust
c. Lift and weight equal thrust and drag

Answer 12

a. Lift equals weight and thrust equals drag

Question 13

Which statement relates to Bernoulli’s principle?

a. For every action, there is an equal and opposite reaction.
b. An additional upward force is generated as the lower surface of the wing deflects air downward.
c. Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface.

Answer 13

c. Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface.

Question 14

Angle between the chord line and relative wind is called?

a. Angle of incidence
b. Angle of attack
c. Dihedral

Answer 14

b. Angle of attack

Question 15

The term angle of attack is defined between the angle of:

a. chord line of the wing and the relative wind.
b. airplane’s longitudinal axis and that of the air striking the airfoil.
c. airplane’s center line and the relative wind.

Answer 15

a. chord line of the wing and the relative wind.

Question 16

The angle between the chord line of an airfoil and the relative wind is known as the angle of:

a. lift
b. attack
c. incidence

Answer 16

b attack

Question 17

The angle of attack at which an airplane wing stalls will:

a. increase if the CG is moved forward.
b. change with an increase in gross weight.
c. remain the same regardless of gross weight.

Answer 17

c. remain the same regardless of gross weight.

Question 18

As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will:

a. decrease as the true airspeed decreases.
b. decrease as the true airspeed increases.
c. remain the same regardless of altitude.

Answer 18

c. remain the same regardless of altitude.

Question 19

In what flight condition must an aircraft be placed in order to spin?

a. Partially stalled with one wing low.
b. In a steep diving spiral.
c. Stalled

Answer 19

c. Stalled.

Question 20

During a spin to the left, which wing is/are stalled?

a. Both wings are stalled.
b. Neither wing is stalled.
c. Only the left wing is stalled.

Answer 20

a. Both wings are stalled.

Question 21

What is ground effect?

a. The results of the interference of the surface of the Earth with the airflow patterns about an airplane.
b. The result of an alteration in airflow patterns increasing induced drag about the wings of an airplane.
c. The result of the disruption of the airflow patterns about the wings of an airplane to the point where the wings will no longer support the airplane in flight.

Answer 21

a. The result of the interference of the surface of the Earth with the airflow patterns about an airplane.

Question 22

Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at:

a. Less than the length of the wingspan above the surface.
b. Twice the length of the wingspan above the surface.
c. Higher than normal angle of attack.

Answer 22

a. Less than the length of the wingspan above the surface.

Question 23

What must a pilot be aware of as a result of ground effect?

a. Wingtip vortices increase creating wake turbulence problems for arriving and departing aircraft.
b. Induced drag decreases; therefore, any excess speed at the point of flare may cause considerable floating.
c. A full stall landing will require less up elevator deflection that would a full stall when done free of ground effect

Answer 23

b. Induced drag decreases; therefore, any excess speed at the point of flare may cause considerable floating.

Question 24

An aircraft leaving ground effect during takeoff will:

a. experience a reduction in ground fiction and require a slight power reduction.
b. experience an increase in induced drag and a decrease in performance.
c. require a lower angle of attack to maintain the same lift coefficient.

Answer 24

b. experience an increase in induced drag and a decrease in performance.

Question 25

Ground effect is most likely to result in which problem?

a. Setting to the surface abruptly during landing.
b. Becoming airborne before reaching recommended takeoff speed.
c. Inability to get airborne even though airspeed is sufficient for normal takeoff needs.

Answer 25

b. Becoming airborne before reaching recommended takeoff speed.

Question 26

What force makes an airplane turn?

a. Horizontal component of lift.
b. Vertical component of lift.
c. Centrifugal force.

Answer 26

a. Horizontal component of lift.

Question 27

What determines the longitudinal of an airplane?

a. The location of the CG with respect to the center of lift.
b. The effectiveness of the horizontal stabilizer, rudder, and rudder trim tab.
c. The relationship of thrust and lift to weight and drag.

Answer 27

a. The location of the CG with respect to the center of lift.

Question 28

An airplane said to be inherently stable will:

a. be difficult to stall.
b. require less effort to control.
c. not spin.

Answer 28

b. require less effort to control.

Question 29

Changes in the center of pressure of a wing affect the aircraft’s:

a. lift/drag ratio
b. lifting capacity
c. aerodynamic balance and controlability

Answer 29

c. aerodynamic balance and controlability

Question 30

An airplane has been loaded in such a manner that the CG is located aft of the aft CG limit. One undesirable flight characteristic a pilot might experience with this airplane would be:

a. a longer takeoff run.
b. difficulty in recovering from a stalled condition.
c. stalling at a higher-than-normal airspeed.

Answer 30

b. difficulty in recovering from a stalled condition.

Question 31

What causes an airplane (except a T-tail) to pitch nose-down when power is reduced and controls are not adjusted?

a. The CG shifts forward when thrust and drag are reduced.
b. The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced.
c. When thrust is reduced to less than weight, lift is also reduced and the wings can no longer support the weight.

Answer 31

b. The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced.

Question 32

What is the effect of advancing throttle in flight?

a. Both aircraft groundspeed and angle of attack will increase.
b. Airspeed will remain relatively constant but the aircraft will climb.
c. The aircraft will accelerate, which will cause a turn to the right.

Answer 32

a. Both aircraft groundspeed and angle of attack will increase.

Question 33

Loading an airplane to the most aft CG will cause the airplane to be:

a. less stable at all speeds.
b. less stable at slow speeds, but more stable at high speeds.
c. less stable at high speeds, but more stable at low speeds.

Answer 33

a. less stable at all speeds.

Question 34

An airplane loaded with the Center of Gravity rear of the aft CG limit could:

a. make it easier to recover from stalls and spins.
b. make it more difficult to flare for landing.
c. increase the likelihood of inadvertent overstress.

Answer 34

c. increase the likelihood of inadvertent overstress.

Question 35

In what flight condition are torque effects more pronounced in a single-engine airplane?

a. Low airspeed, high power, high angle of attack.
b. Low airspeed, low power, low angle of attack.
c. High airspeed, high power, high angle of attack.

Answer 35

a. Low airspeed, high power, high angle of attack.

Question 36

The left turning tendency of an airplane caused by P-factor is the result of the:

a clockwise rotation of the engine and the propeller turning the airplane counterclockwise.

b. propeller blade descending on the right, producing more thrust than the ascending blade on the left.
c. gyroscopic forces applied to rotating propeller blades acting 90 degrees in advance of the point the force was applied.

Answer 36

b. propeller blade descending on the right, producing more thrust than the ascending blade on the left.

Question 37

When does p-factor cause the airplane to yaw to the left?

a. when at low angles of attack.
b. when at high angles of attack.
c. when at high airspeeds.

Answer 37

b. high angles of attack.

Question 38

Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level-flight?

a. Climb
b. Turn
C. Stall

Answer 38

b. Turn

Question 39

The amount of excess load that can be imposed on the wing of an airplane depends upon the

a. position of CG
b. speed of airplane
c. abruptness at which the load is applied

Answer 39

b. speed of airplane

Question 40

During an approach to a stall, an increased load factor will cause the aircraft to:

a. stall at a higher airspeed
b. have a tendency to spin
c. be more difficult to control

Answer 40

a. stall at a higher airspeed.

Question 41

Structural damage or failure is more likely to occur in smooth air at speeds above:

a. VNO - maximum structural cruising speed
b. VA - maneuvering speed
c. VNE - never exceed speed

Answer 41

c. VNE - never exceed speed

Question 42

Limit load factor is the ratio of

a. angle of attack to stall speed
b. angle of attack to power-on-configuration specific stall speed
c. maximum sustainable load to the gross weight of the airplane

Answer 42

c. maximum sustainable load to the gross weight of the airplane

Question 43

If an airplane weighs 3300pounds, what approximate weight would the airplane structure be required to support during a 30 degree banked turn while maintaining altitude?

Answer 43

3960pounds

Question 44

If an airplane weighs 2,300 pounds, what approximate weight would the airplane structure be required to support during a 60degree banked turn while maintaining altitude?

Answer 44

4600pounds

Question 45

If an airplane weighs 4500pounds, what approximate weight would the airplane structure be required to support during a 45degree banked turn while maintaining altitude.

Answer 45

6750pounds

Question 46

A positive load factor of 2 at 80mph would cause the airplane to:

a. stall
b. break apart.
c. operate normally, as it is within the normal operating range.

Answer 46

a. stall

Question 47

What load factor would be created if positive 15 feet per second gusts were encountered at 120mph?

Answer 47

2.0

Question 48

The airspeed indicated by points A and J is:

Answer 48

normal stall speed