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66 Cards in this Set

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One of the main functions of flaps during the approach and landing is to
provide the same amount of lift at a slower airspeed
Which is true regarding the use of flaps during level turns
the raising of flaps increases the stall speed
A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the
wing root, with the stall progression toward the wingtip
The angle of attack of a wing directly controls the
distribution of pressure acting on the wing
Frost covering the upper surface of an airplane wing usually will cause
the airplane to stall at an angle of attack that is lower than normal
By changing the angle of attack of a wing, the pilot can control the airplane's
lift, airspeed, and drag
The critical angle of attack is exceeded when
a stall occurs
The angle of attack at which a wing stalls remains constant regardless of
weight, dynamic pressure, bank angle, or pitch attitude
the need to slow an aircraft below Va is brought about by following weather phenomenon
turbulence which causes an increase in stall speed
Stall speed is affected by
weight, load factor, and power
An airplane will stall at the same
angle of attack regardless of the attitude with relation to the horizon
In rapid recovery from a dive, the effects of load factor would cause the stall speed to
increase
The stalling speed of an airplane is most affected by
variations in airplane loading
(Refer to figure 2 below) Select the correct statement regarding stall speeds
power-on stalls occur at lower airspeeds in shallower banks
(Refer to figure 2) Select the correct statement regarding stall speeds. The airplane will stall
10 knots higher in a power-on, 60' bank, with gear and flaps up, than with gear and flaps down
Recovery from a stall in any airplane becomes more difficult when its
center of gravity moves aft
In small airplanes, normal recovery from spins may become difficult if the
CG is too far rearward, and rotation is around the CG
Which statement is true relative to changing angle of attack
an increase in angle of attack will increase drag
To generate the same amount of lift as altitude is increased, an airplane must be flown at
a higher true airspeed for any given angle of attack
As angle of bank is increased, the vertical component of lift
decreases and the horizontal component of lift increases
Which is true regarding the forces acting on an aircraft in a steady-state descent? the sum of all
forward forces is equal to the sum of all rearward forces
during the transition from straight-and-level flight to a climb, the angle of attack is increased and lift
is momentarily increased
What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased
increase the angle of attack to compensate for the decreasing lift
Which is true regarding the force of lift in steady, unaccelerated flight
There is a corresponding indicated airspeed required for every angle of attack to generate sufficent lift to maintain altitude
In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become
four times greater
As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane
increases because of increased induced drag
Which performance is characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? maximum
range and maximum distance glide
In theory, if the angle of attack and other factors remain constant and the airspeed is doubled, the lift produced at the higher speed will be
four times greater than at the lower speed
An aircraft wing is designed to produce lift resulting from a difference in the
higher air pressure below the wing's surface and lower air pressure above the wing's surface
(Refer to figure 3 on page 33) if an airplane glides at an angle of attack of 10', how much altitude will it lose in 1 mile
480 mile
(Refer to figure 3 below) how much altitude will this airplane lose in 3 statute miles of gliding at an angle of attack of 8'?
1,320 feet
(refer ti figure 3 above) The L/D ratio at a 2' angle of attack is approximately the same as the L/D ratio for a
16.5' angle of attack
Lift on a wing is most properly defined as the
force acting perpendicular to the relative wind
(Refer to figure 1 above) At an airspeed represented by point B, in steady flight, the pilot can expect to obtain the airplane's maximum
glide range
(Refer to figure 1 above) at the airspeed represented by point A, in steady flight, the airplane will
have its maximum L/D ratio
On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the
flightpath
Which statement is true regarding the opposing forces acting on an airplane in steady-state level flight?
these forces are equal
An airplane leaving ground effect will
experience an increase in induced drag and require more thrust
To produce the same lift while in ground effect as when out of ground effect, the airplane requires
a lower angle of attack
If the same angle of attack is maintained in ground effect as when out of ground effect, lift will
increase, and induced drag will decrease
Longitudinal stability involves the motion of the airplane controlled by its
elevator
Longitudinal dynamic instability in an airplane can be identified by
pitch oscillations becoming progressively steeper
If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays
neutral longitudinal static stability
If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays
positive static stability
If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its
lateral axis
If airspeed is increased during a level turn, what action would be necessary to maintain altitude? the angle of attack
must be decreased or angle of bank increased
If a standard rate turn is maintained, how long would it take to turn 360'
2 minutes
While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would
remain constant regardless of air density and the resultant lift vector
To increase the rate of turn and at the same time decrease the radius, a pilot should
Increase the bank and decrease airspeed
Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?
for a specific angle of bank and airspeed, the rate and radius of turn will not vary
While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will
decrease the rate of turn resulting in no change in load factor
Why is it necessary to increase back elevator pressure to maintain altitude during a turn? to compensate for the
loss of the vertical component of lift
To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the
vertical component of lift
The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flgiht is known as
load factor and directly affects stall speed
Load factor is the lift generated by the wings of an aircraft at any given time
divided by the total weight of the aircraft
For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn
is constant and the stall speed increases
Airplane wing loading during a level coordinated turn in smooth air depends upon the
angle of bank
(Refer to figure 4 below) What increases in load factor would take place if the angle of bank were increased from 60' to 80'
4 G's
(Refer to figure 4 below) What is the stall speed of an airplane under a load factor of 2 G's if the unaccelerated stall speed is 60 knots
84 knots
If an aircraft with a gross weight of 2,000 pounds was subjected to a 60' constant-altitude bank, the total load would be
4,000 pounds
If the airspeed is increase from 90 knots to 135 knots during a level 60' banked turn, the load factor will
remain the same but the radius of turn will increase
Baggage weighting 90 knots pounds is placed in a normal category airplane's baggage compartment which is placarded at 100 pounds. If this airplane is subjected to a positive load factor of 3.5 G's, the total load of baggage would be
315 pounds and would not be excessive
Which factor below is the best indication of positive or negative G's in an aircraft
change in how heavy or light you feel in your seat
Transonic airflow typically occurs in airplane speed regimes between Mach
0.75 and 1.20
Accelerating past critical Mach may result in the onset of compressibility effects such as
control difficulties
Acceleration past critical Mach speed may cause compressibility issues such as
drag increases