Chapter 1 Gleim

Airplanes and aerodynamics

What is the purpose of wing flaps?

to enable the pilot to make steeper approaches to a landing w/o increasing the airspeed.

1 of the main functions of flaps during approach and landing is to

increase the angle of descent w/o increasing the airspeed

what is the purpose of the rudder on an airplane?

To control yaw?

which is not a primary flight control surface?

flaps

the elevator controls movement around which axis?

Lateral

which statement is true concerning primary flight controls?

the effectiveness of each control surface increases with speed bc there is more airflow over them.

which of the following is true concerning flaps?

flaps allow an increase in the angle of descent w/o increasing airspeed

which device is a secondary flight control?

spoilers

trim systems are designed to do what?

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

the four forces acting on an airplane in flight are

lift, weight, thrust, and drag

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

during unaccelerated level flight

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

which statement relates to Bernoullis principle?

air travelling faster over the curved upper surface of an airfoil causes lower pressure on the top surface

(refer to figure 1) the acute angle A is the angle of

attack

the term “angle of attack” is defined as the angle between the

chord line of the wing and he relative wind

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

attack

the angle of attack at which an airplane wing stalls will

remain the same regardless of gross weight

as attitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will

remain the same regardless of altitude

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

stalled

during a spin to the left which wing(s) is/are stalled?

both wings are stalled

what is ground effect?

the rsult of the interference of the surface of the earth w/ the airflow patterns about an airplane

floating caused by the phenominon of ground effect will be most realized during an approach to land when at

less than the length of the wingspan above the surface

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

induced drag increases, therefore, any excess speed at the point of flare may cause considerable floating

an aircraft leaving ground effect during takeoff will

experience an increase in induced drag and a decrease in performance

ground effect is most likely to result in which problem?

becoming airborne before reaching recommended take off speed

what force makes an airplane turn?

the horizontal component of lift

what determines the longitudinal stability of an airplane?

the location of the CG with respect to the center of lift

an airplane said to be inherently stable will

require less effort to control

changes in the center of pressure of a wing affect the aircrafts

aerodynamic balance and controllability

an airplane has been load in such a manner the the CG is located aft of the aft CG limit. One undesirable flight characteristic a pilot might experience w/ this airplane would be

difficulty in recovering from a stalled condition

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

what is the effect of advancing the throttle in flight?

both aircraft groundspeed and angle of attack will increase

loading an airplane to the most aft CG will cause the airplane to be

less stable at all speeds

an airplane loaded w/ the center of gravity (CG) rear of the aft CG limit could

increase the likelihood of inadvertant overstress

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

low airspeed, high power, high angle of attack

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

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

when does P-factor cause the airplane to yaw to the left?

when at high angles of attack

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

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

which of the following is not a left-turning tendency at hih power during takeoff?

gyroscopic precession in a tricycle gear airplane

(refer to figure 2 below) if an airplane weighs 3,300 pounds, what approximate weight would the airplane structure be required to support during a 30 degree banked turn while maintaining attitude?

3,960 pounds

(refer to figure 2 below) 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

(refer to figure 2 below) if an airplane weighs 4,500 pounds, what approximate weight would the airplane structure be required to support during a 45 degree banked turn while maintaining altitude?

6,750 pounds

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

turns

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

speed of the airplane

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

stall at a higher airspeed

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

Vne

limit load factor is the ratio of

maximum sustainable load to the gross weight of the airplane

(refer to figure 72 below) A positive load factor of 2 at 80 mph would cause the airplane to

stall

(refer to figure 72 below) what load factor would be created if positive 15 feet per second gusts were encountered at 120mph?

2.0

(refer to figure 72 below) the airspeed indicated by points A and J is

normal stall speed