Aerodynamics

8377. What will be the ratio between airspeed and lift if the angle of attack and other factors remain constant and airspeed is doubled? Lift will be: A. The same. B. Two times greater. C. Four times greater.

8378. What true airspeed and angle of attack should be used to generate the same amount of lift as altitude is increased?. A. The same true airspeed and angle of attack. B. A higher true airspeed for any given angle of attack. C. A lower true airspeed and higher angle of attack.

8348. What affects indicated stall speed?. A. Weight, load factor, and power. B. Load factor, angle of attack, and power. C. Angle of attack, weight, and air density.

9808. The stall speed of an airplane. A. Is constant regardless of weight or airfoil configuration. B. Is affected by weight, and bank angle. C. Is not affected by dynamic pressures and lift coefficient.

8346. What is the effect on total drag of an aircraft if the airspeed decreases in level flight below that speed for maximum L/D?. A. Drag increases because of increased induced drag. B. Drag increases because of increased parasite drag. C. Drag decreases because of lower induced drag.

9942. How does the stall speed (KCAS) vary as you climb from sea level to 33,000 feet?. A. It varies directly with a change in altitude. B. It remains relatively unchanged throughout the climb. C. It varies indirectly with a change in altitude.

8397. What is the relationship between induced and parasite drag when the gross weight is increased?. A. Parasite drag increases more than induced drag. B. Induced drag increases more than parasite drag. C. Both parasite and induced drag are equally increased.

9767. How does Vs (KTAS) speed vary with altitude?. A. Remains the same at all altitudes. B. Varies directly with altitude. C. Varies inversely with altitude.

8368. What is the reason for variations in geometric pitch along a propeller or rotor blade?. A. It permits a relatively constant angle of attack along its length when in cruising flight. B. It prevents the portion of the blade near the hub or root from stalling during cruising flight. C. It permits a relatively constant angle of incidence along its length when in cruising flight.

8375. What flight condition should be expected when an aircraft leaves ground effect?. A. An increase in induced drag requiring a higher angle of attack. B. A decrease in parasite drag permitting a lower angle of attack. C. An increase in dynamic stability.

8382. By changing the angle of attack of a wing, the pilot can control the airplane's. A. Lift, gross weight, and drag. B. Lift, airspeed, and drag. C. Lift and airspeed, but not drag.

8399. At which speed will increasing the pitch attitude cause an airplane to climb?. A. Low speed. B. High speed. C. Any speed.

8379. How can an airplane produce the same lift in ground effect as when out of ground effect?. A. The same angle of attack. B. A lower angle of attack. C. A higher angle of attack.

8357. In a light, twin-engine airplane with one engine inoperative, when is it acceptable to allow the ball of a slip-skid indicator to be deflected outside the reference lines?. A. While maneuvering at minimum controllable airspeed or less to avoid overbanking. B. When operating at any speed of Vmc or greater with only enough deflection to zero the side slip. C. When practicing imminent stalls in a banked attitude of over 60°.

8358. What is the safest and most efficient takeoff and initial climb procedure in a light, twin-engine airplane? Accelerate to. A. Best engine-out, rate-of-climb airspeed while on the ground, then lift off and climb at that speed. B. Vmc, then lift off at that speed and climb at maximum angle-of-climb airspeed. C. An airspeed slightly above Vmc, the lift off and climb at the best rate-of-climb airspeed.

8360. What performance should a pilot of a light, twin-engine airplane be able to maintain at Vmc?. A. Heading. B. Heading and altitude. C. Heading, altitude, and ability to climb 50 ft/min.

8364. What does the blue radial line on the airspeed indicator of a light twin-engine airplane represent?. A. Maximum single-engine rate of climb. B. Maximum single-engine angle of climb. C. Minimum controllable airspeed for single-engine operation.

8359. What procedure is recommended for an engine-out approach and landing?. A. The flightpath and procedures should be almost identical to a normal approach and landing. B. The altitude and airspeed should be considerably higher than normal throughout the approach. C. A normal approach, except do not extend the landing gear or flaps until over the runway threshold.

8361. Which engine is the "critical" engine of a twin-engine airplane?. A. The one with the center of thrust closest to the centerline of the fuselage. B: The one designated by the manufacturer which develops most usable thrust. C. The one with the center pf thrust farthest from the centerline of the fuselage.

8362. What effect, if any, does altitude have on Vmc for an airplane with unsuperchaged engines?. A. None. B. Increases with altitude. C. Decreases with altitude.

8363. Under what conditions should stalls never be practiced in a twin-engine airplane?. A. With one engine inoperative. B. With climb power on. C. With full flaps and gear extended.

8349. If no corrective action is taken by the pilot as angle of bank is increased, how is the vertical component of lift and sink rate affected?. A. Lift increases and the sink rate increases. B. Lift decreases and the sink rate decreases. C. Lift decreases and the sink rate increases.

8350. Why must the angle of attack be increased during a turn to maintain altitude?. A. Compensate for loss of vertical component of lift. B. Increase the horizontal component of lift equal to the vertical component. C. Compensate for increase in drag.

8347. What is load factor?. A. Lift multiplied by the total weight. B. Lift subtracted from the total weight. C. Lift divided by the total weight.

9823. During a turn with constant power. A. The aircraft nose will pitch down. B. The aircraft will decelerate. C. The rate of descent will increase.

9740. During a skidding turn to the right, what is the relationship between the component of lift and centrifugal force?. A. Centrifugal force is less than the horizontal lift component and the load factor is increased. B. Centrifugal force is greater than the horizontal lift component. C. Centrifugal force and the horizontal lift component are equal, and the load factor is decreased.

8354. If an aircraft with a gross weight of 2,000 pounds were subjected to a total load of 6,000 pounds in flight, the load factor would be. A. 2 G's. B. 3 G's. C. 9 G's.

8353. Upon which factor does wing loading during a level coordinated turn in smooth air depend?. A. Rate of turn. B. Angle of bank. C. True airspeed.

8396. For a given angle of bank, the load factor imposed on both the aircraft and pilot in a coordinated constant altitude turn. A. Increases with an increase in airspeed. B. Remains constant regardless of airspeed changes. C. Decreases with an increase in airspeed.

8351. How can the pilot increase the rate of turn and decrease the radius of turn at the same time?. A. Steepen the bank and increase airspeed. B. Steepen the bank and decrease airspeed. C. Shallow the bank and increase airspeed.

8352. What is the relationship of the rate of turn with the radius of turn with a constant angle of bank but increasing airspeed?. A. Rate will decrease and radius will increase. B. Rate will increase and radius will decrease. C. Rate and radius will increase.

8345. What effect does an increase in airspeed have on a coordinated turn while maintaining a constant angle of bank and altitude?. A. The rate of turn will decrease resulting in a decreased load factor. B. The rate of turn will increase resulting in an increased load factor. C. The rate of turn will decrease resulting in no changes in load factor.

8345-1. Generally, the turning performance of an airplane is defined by. A. Structural and power limits at high altitude. B. Aerodynamic and structural limits at low altitude. C. Control and structural limits at high altitude.

8345-2. A bank angle of 15° will increase induced drag by about. A. 3%. B. 7%. C. 15%.

8365. Identify the type stability if the aircraft attitude remains in the new position after the controls have been neutralized. A. Negative longitudinal static stability. B. Neutral longitudinal dynamic stability. C. Neutral longitudinal static stability.

8372. Identify the type stability if the aircraft attitude tends to move farther from its original position after the controls have been neutralized. A. Negative static stability. B. Positive static stability. C. Negative dynamic stability.

8373. Identify the type stability if the aircraft attitude tends to return to its original position after the controls have been neutralized. A. Positive dynamic stability. B. Positive static stability. C. Neutral dynamic stability.

*8366. What is a characteristic of longitudinal instability?. A. Pitch oscillations becoming progressively greater. B. Bank oscillations becoming progressively greater. C. Aircraft constantly tries to pitch down.

*8367. Describe dynamic longitudinal stability. A. Motion about the longitudinal axis. B. Motion about the lateral axis. C. Motion about the vertical axis.

8376. What characteristic should exist if an airplane is loaded to the rear of its CG range?. A. Sluggish in aileron control. B. Sluggish in rudder control. C. Unstable about the lateral axis.

8380. What are some characteristics of an airplane loaded with the CG at the aft limit?. A. Lowest stall speed, highest cruise speed, and least stability. B. Highest stall speed, highest cruise speed, and least stability. C. Lowest stall speed, lowest cruise speed, and highest stability.

9921. An airplane loaded with the CG aft of the rear 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.

8387. Within what Mach range does transonic flight regimes occur?. A. .50 to .75 Mach. B. .75 to 1.20 Mach. C. 1.20 to 2.50 Mach.

8390. At what Mach range does the subsonic flight range normally occur?. A. Below .75 Mach. B. From .75 to 1.20 Mach. C. From 1.20 to 2.50 Mach.

8388. What is the highest possible speed without supersonic flow over the wing?. A. Initial buffet speed. B. Critical Mach Number. C. Transonic index.

8389. What is the free stream Mach number which produces first evidence of local sonic flow?. A. Supersonic Mach number. B. Transonic Mach number. C. Critical Mach number.

8392. What is the result of a shock-induced separation of airflow occurring symmetrically near the wing root of a sweptwing aircraft?. A. A high-speed stall and sudden pitchup. B. A severe moment or "Mach tuck". C. Severe porpoising.

8395. What is the movement of the center of pressure when the wingtips of a sweptwing airplane are shock-stalled first?. A. Inward and aft. B. Inward and forward. C. Outward and forward.

8391. What is the principal advantage of a sweepback design wing over a straightwing design?. A. The critical Mach number will increase significantly. B. Sweepback will increase changes in the magnitude of force coefficients due to compressibility. C. Sweepback will accelerate the onset of compressibility effect.

8391-1. Swept wings. A. Improve specific fuel consumption. B. Increase the critical Mach number. C. Increase the speed of sound quotient.

8391-2. For significant benefit, wing sweep must be at least. A. 30 to 35°. B. 45 to 50°. C. 55° or more to substantially delay compressibility effects.

8393. What is one disadvantage of sweptwing design?. A. The wing root stalls prior to the wingtip section. B. The wingtip section stalls prior to the wing root. C. Severe pitchdown moment when the center of pressure shifts forward.

9803. Swept wings cause a significant. A. Increase in effectiveness of flaps. B. Reduction in effectiveness of flaps. C. Flap actuation reliability issue.

*8394-2. A turbojet airplane has an increase in specific rance with altitude, which can be attributed to three factors. One of those factors is. A. An increase in altitude in the troposphere results in higher energy airflow. B. An increase in proportion versus thrust required. C. Decreased engine turbine speeds.