FAA PRIVATE
PILOT 2024 TEST
PREP CHAPTER 1
3203. (Refer to Figure 1.) The acute angle A is the angle of
attack.
3204. The term "angle of attack" is defined as the angle
between the wing chord line and the relative wind.
3204-1. The angle between the chord line of an airfoil and the relative wind is know as
the angle of
attack.
3317. The term angle of attack is defined as the angle between the
chord line of the wing and the relative wind.
3201-1. Which statement relates to Bernoulli's principle?
Air traveling faster over the curved upper surface of an airfoil causes lower pressure on
the top surface.
3201. The four forces acting on an airplane in flight are
lift, weight, thrust, and drag.
, 3213. What is the purpose of the rudder on an airplane?
To control yaw.
3205. What is the relationship of lift, drag, thrust, and weight, when the airplane is in
straight-and-level flight?
Lift equals weight and thrust equals drag.
3202. When are the four forces that act on an airplane in equilibrium?
During unaccelerated flight.
3210. An airplane said to be inherently stable will
require less effort to control.
3211. What determines the longitudinal stability of an airplane?
The location of the CG with respect to the center of lift.
3212. What causes an airplane (except a T-tail) to pitch nosedown when power is
reduced and controls are not adjusted?
The downwash on the elevators from the propeller slipstream is reduced and elevator
effectiveness is reduced.
3287. 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
difficulty in recovering from a stalled condition.
3288. Loading an airplane to the most aft CG will cause the airplane to be
less stable at all speeds.
3211-1. Changes in the center of pressure of a wing affect the aircraft's
aerodynamic balance and controllability.
3214. (Refer to Figure 2.) If an airplane weighs 2,300 pounds, what approximate weight
would the airplane structure be required to support during a 60 degree banked turn
while maintaining altitude?
4,600 pounds.
PILOT 2024 TEST
PREP CHAPTER 1
3203. (Refer to Figure 1.) The acute angle A is the angle of
attack.
3204. The term "angle of attack" is defined as the angle
between the wing chord line and the relative wind.
3204-1. The angle between the chord line of an airfoil and the relative wind is know as
the angle of
attack.
3317. The term angle of attack is defined as the angle between the
chord line of the wing and the relative wind.
3201-1. Which statement relates to Bernoulli's principle?
Air traveling faster over the curved upper surface of an airfoil causes lower pressure on
the top surface.
3201. The four forces acting on an airplane in flight are
lift, weight, thrust, and drag.
, 3213. What is the purpose of the rudder on an airplane?
To control yaw.
3205. What is the relationship of lift, drag, thrust, and weight, when the airplane is in
straight-and-level flight?
Lift equals weight and thrust equals drag.
3202. When are the four forces that act on an airplane in equilibrium?
During unaccelerated flight.
3210. An airplane said to be inherently stable will
require less effort to control.
3211. What determines the longitudinal stability of an airplane?
The location of the CG with respect to the center of lift.
3212. What causes an airplane (except a T-tail) to pitch nosedown when power is
reduced and controls are not adjusted?
The downwash on the elevators from the propeller slipstream is reduced and elevator
effectiveness is reduced.
3287. 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
difficulty in recovering from a stalled condition.
3288. Loading an airplane to the most aft CG will cause the airplane to be
less stable at all speeds.
3211-1. Changes in the center of pressure of a wing affect the aircraft's
aerodynamic balance and controllability.
3214. (Refer to Figure 2.) If an airplane weighs 2,300 pounds, what approximate weight
would the airplane structure be required to support during a 60 degree banked turn
while maintaining altitude?
4,600 pounds.
