AVIATION 170 SDSU- CH1: Aero

(5205) In small airplanes, normal recovery from spins may become difficult if the ____.

*a. CG is too far rearward and rotation is around the CG. b. spin is entered before the stall is fully developed. c. CG is too far rearward and rotation is around the longitudinal axis.

(5213) (Refer to Figure 3.) If an airplane glides at an angle of attack of 10°, how much altitude will it lose in 1 mile [11:1 glide ratio]?

*a. 480 feet. b. 960 feet. c. 240 feet.

(5220.1) To hold an airplane in level flight at airspeeds from very slow to very fast, a pilot must coordinate thrust and ____.

*a. angle of attack. b. angle of incidence. c. gross weight.

(5157) While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will ____.

*a. decrease the rate of turn resulting in no change in load factor. b. increase the rate of turn resulting in no change in load factor. c. decrease the rate of turn resulting in a decreased load factor.

(5158) Lift on a wing is most properly defined as the ____.

*a. force acting perpendicular to the relative wind. b. reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber. c. differential pressure acting perpendicular to the chord of the wing.

(5226) If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays____.

*a. neutral longitudinal static stability. b. positive longitudinal static stability. c. neutral longitudinal dynamic stability.

(5227) Longitudinal dynamic instability in an airplane can be identified by

*a. pitch oscillations becoming progressively steeper. b. Trilatitudinal roll oscillations becoming progressively steeper. c. bank oscillations becoming progressively steeper.

(5230) If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays____.

*a. positive static stability. b. neutral dynamic stability. c. positive dynamic stability.

(5195) To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the ____.

*a. vertical component of lift. b. horizontal component of lift. c. forces opposing the resultant component of drag.

(5156) (Refer to Figure 4.) If an aircraft with a gross weight of 2,000 pounds was subjected to a 60° constant-altitude bank, the total load would be ____.

a. 12,000 pounds. *b. 4,000 pounds. c. 3,000 pounds.

(5222) (Refer to Figure 4.) What increase in load factor would take place if the angle of bank were increased from 60° to 80°?

a. 3.5 Gs. *b. 4 Gs. c. 3 Gs.

(5221) (Refer to Figure 4.) What is the stall speed of an airplane under a load factor of 2 Gs if the unaccelerated stall speed is 60 knots?

a. 66 knots. *b. 84 knots. c. 74 knots.

(5167) Which statement is true relative to changing angle of attack?

a. A decrease in angle of attack will increase pressure below the wing, and decrease drag. b. An increase in angle of attack will decrease pressure below the wing, and increase drag. *c. An increase in angle of attack will increase drag.

(5977) What is the best indicator to the pilot of the load factor on the airplane?

a. Airspeed when pulling out of a descent. b. Amount of pressure required to operate the controls. *c. How firmly the pilot is pressed into the seat during a maneuver.

(5219) Which is true regarding the force of lift in steady, unaccelerated flight?

a. At lower airspeeds the angle of attack must be less to generate sufficient lift to maintain altitude. *b. There is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude. c. An airfoil will always stall at the same indicated airspeed; therefore, an increase in weight will require an increase in speed to generate sufficient lift to maintain altitude.

(5655) Which is true with respect to vortex circulation in the wake turbulence generated by an aircraft?

a. Helicopters generate downwash turbulence only, not vortex circulation. b. When vortex circulation sinks into ground effect, it tends to dissipate rapidly and offer little danger. *c. The vortex strength is greatest when the generating aircraft is heavy, clean, and slow.

(5179) (Refer to Figure 2.) Select the correct statement regarding stall speeds.

a. In a 60° bank the airplane stalls at a lower airspeed with the gear up. b. Power-off stalls occur at higher airspeeds with the gear and flaps down. *c. Power-on stalls occur at lower airspeeds in shallower banks.

(5181) Which is true regarding the use of flaps during level turns?

a. Raising flaps will require added forward pressure on the yoke or stick. b. The lowering of flaps increases the stall speed. *c. The raising of flaps increases the stall speed.

(5203) Which statement is true, regarding the opposing forces acting on an airplane in steady-state level flight?

a. Thrust is greater than drag and weight and lift are equal. *b. These forces are equal. c. Thrust is greater than drag and lift is greater than weight.

(5224) To produce the same lift while in ground effect as when out of ground effect, the airplane requires____.

a. a greater angle of attack. *b. a lower angle of attack. c. the same angle of attack.

(5223) To generate the same amount of lift as altitude is increased, an airplane must be flown at____.

a. a lower true airspeed and a greater angle of attack. *b. a higher true airspeed for any given angle of attack. c. the same true airspeed regardless of angle of attack.

(5231) (Refer to Figure 5.) The horizontal dashed line from point C to point E [max load, 3.8Gs] represents the ____.

a. airspeed range for normal operations. b. ultimate load factor. *c. positive limit load factor.

(5212) An airplane will stall at the same____.

a. angle of attack and attitude with relation to the horizon. *b. angle of attack regardless of the attitude with relation to the horizon. c. airspeed regardless of the attitude with relation to the horizon.

(5196) Stall speed is affected by ____.

a. angle of attack, weight, and air density. *b. weight, load factor, and power. c. load factor, angle of attack, and power.

(5220) When transitioning from straight-and-level flight to a constant airspeed climb, the angle of attack and lift ____.

a. are increased and remain at a higher lift-to-weight ratio to maintain the climb. *b. are momentarily increased and lift returns to a steady state during the climb. c. remain the same and maintain a steady state lift-to-weight ratio during the climb.

(5211) The stalling speed of an airplane is most affected by ____.

a. changes in air density. b. variations in flight altitude. *c. variations in airplane loading.

(5202) On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the ____.

a. chord line. b. longitudinal axis. *c. flightpath.

(5182) One of the main functions of flaps during the approach and landing is to____.

a. decrease lift, thus enabling a steeper-than-normal approach to be made. *b. provide the same amount of lift at a slower airspeed. c. decrease the angle of descent without increasing the airspeed.

(5978) If the airspeed is decreased from 98 knots to 85 knots during a coordinated level 45 degree banked turn, the load factor will ____.

a. decrease, and the rate of turn will decrease. *b. remain the same, but the radius of turn will decrease. c. remain the same, but the radius of turn will increase.

(5204) The angle of attack at which a wing stalls remains constant regardless of ____.

a. dynamic pressure, but varies with weight, bank angle, and pitch attitude. b. weight and pitch attitude, but varies with dynamic pressure and bank angle. *c. weight, dynamic pressure, bank angle, or pitch attitude.

(5166) (Refer to Figure 1.) At an airspeed represented by point B [greatest lift/drag ratio], in steady flight, the pilot can expect to obtain the airplane's maximum____.

a. endurance. *b. glide range. c. coefficient of lift.

(5163.1) A load factor of 1.2 means the total load on an aircraft's structure is 1.2 times its ____.

a. gust factor. *b. gross weight. c. load limit.

(5153) For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn ____.

a. is constant and the stall speed decreases. b. varies with the rate of turn. *c. is constant and the stall speed increases.

(5210) If airspeed is increased during a level turn, what action would be necessary to maintain altitude? The angle of attack ____.

a. must be increased or angle of bank decreased. *b. must be decreased or angle of bank increased. c. and angle of bank must be decreased.

(5194) Why is it necessary to increase back elevator pressure to maintain altitude during a turn? To compensate for the____.

a. rudder deflection and slight opposite aileron throughout the turn. b. loss of the horizontal component of lift and the increase in centrifugal force. *c. loss of the vertical component of lift.

(5218) Which is true regarding the forces acting on an aircraft in a steady-state descent? The sum of all

a. upward forces is less than the sum of all downward forces. b. rearward forces is greater than the sum of all forward forces. *c. forward forces is equal to the sum of all rearward forces.

(5201) An aircraft wing is designed to produce lift resulting from a difference in the____.

a. vacuum below the wing's surface and greater air pressure above the wing's surface. *b. higher air pressure below the wing's surface and lower air pressure above the wing's surface. c. negative air pressure below and a vacuum above the wing's surface.

(5159) While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would____.

a. vary depending upon speed and air density provided the resultant lift vector varies proportionately. *b. remain constant regardless of air density and the resultant lift vector. c. vary depending upon the resultant lift vector.

(5207) If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its ____.

a. vertical axis. b. longitudinal axis. *c. lateral axis.

(5197) A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the ____.

a. wingtip, with the stall progression toward the wing root. b. center trailing edge, with the stall progression outward toward the wing root and tip. *c. wing root, with the stall progression toward the wing tip.