Which of the following statements regarding energy is true?
A. Kinetic energy decreases with increasing airspeed
B. Potential energy is approximately proportional to airspeed
C. Chemical Energy remains constant throughout flight
D. Kinetic energy can be traded for potential energy and pot...
ATP-CTP course test Latest Updated
Which of the following statements regarding energy is true? A. Kinetic energy decreases with increasing airspeed B. Potential energy is approximately proportional to airspeed C. Chemical Energy remains constant throughout flight D. Kinetic energy can be traded for potential energy and potential energy can be traded for kinetic energy - ANSWER-D. Kinetic energy can be traded for potential energy and potential energy can be traded for kinetic energy
The objective in maneuvering the airplane is to manage the energy so that: A. Kinetic energy stays between limits (stall and placards) B. Potential energy stays between limits (terrain and buffet altitude) C. Chemical energy stays above certain thresholds (not running out of fuel) D. All of the above - ANSWER-D. All of the above
What is the effect on total drag if airspeed slows below L/DMax? A. Drag increases because of increased parasite drag. B. Drag decreases because of lower induced drag. C. Drag increases because of increased induced drag. - ANSWER-C. Drag increases because of increased induced drag
A jet pilot flying at L/DMax will obtain best: A. Range B. Endurance C. Ride Quality - ANSWER-B. Endurance
When a jet aircraft is flown at the appropriate airspeed for maximum range, which type of drag predominates? a. Parasite b. Induced c. Each type of drag contributes equally - ANSWER-a. Parasite
While already at high speed, what happens if Mach is allowed to increase? a. Airflow over parts of the airplane begin to exceed the speed of sound b. Shock waves can cause local airflow separation c. Characteristics such as pitch-up, pitch-down, or buffeting may occur. d. All of the above - ANSWER-d. All of the above What is the result of a shock-induced separation of airflow occurring symmetrically near the wing root of a swept wing aircraft? a. A high-speed stall and sudden pitch-up b. Severe porpoising. c. A severe moment or "Mach Tuck". - ANSWER-c. A severe moment or "Mach Tuck".
The speed of sound generally decreases with increasing altitude. This occurs because: a. The air temperature decreases. b. The air pressure decreases. c. The composition of the air changes. - ANSWER-a. The air temperature decreases.
Critical Mach number can be defined as: a. The speed at which the aircraft is traveling faster than sound. b. The maximum Mach number at which an aircraft may be safely operated. c. the speed of an aircraft in which airflow over any part of the aircraft or structure first reaches, but doesn't exceed, Mach 1.0 - ANSWER-c. the speed of an aircraft in which airflow over any part of the aircraft or structure first reaches, but doesn't exceed, Mach 1.0
Stability in the vertical axis tends to drive the sideslip angle toward zero. The most dynamic stability about the vertical axis on modern jet transports is from: a. The vertical fin b. The rudder c. An active stability augmentation system/yaw damper d. Pilot roll input - ANSWER-c. An active stability augmentation system/yaw damper
Swept wings cause a significant: a. increase in effectiveness of flaps. b. Reduction in effectiveness of flaps c. flap actuation reliability issue - ANSWER-b. Reduction in effectiveness of flaps
Why is convergence of Stall AOA and MMO hazardous? a. Any decrease in airspeed will cause the aircraft to buffet and potentially stall
b. Any increase in airspeed will cause the aircraft to buffet and potentially cause Mach Tuck c. Airspeed changes may occur due to environmental factors, without pilot input. d. All of the above - ANSWER-d. All of the above To maintain altitude in a banked turn, the lift produced by an airplane must be: a. Greater than the airplane weight, and the amount is a function of bank angle b. Greater than the airplane weight, and the amount is a function of altitude c. Equal to the weight of the airplane - ANSWER-a. Greater than the airplane weight, and the amount is a function of bank angle
Excessive bank angles at high altitudes can be hazardous because: a. The extra drag produced by the turn can lead to an excursion below L/DMax b. Aircraft engines at higher altitudes produce less thrust to overcome drag c. The aircraft will be operating closer to its buffet boundaries d. All of the above - ANSWER-d. All of the above
When operating at a constant airspeed with a contact thrust setting at high
altitude (typically above FL250) in slow flight below L/DMax airspeed, any disturbance
causing decrease in airspeed will result in a further decrease in airspeed unless thrust
in increased. High altitude recovery from slow flight while turning is best
accomplished by:
a. Increasing thrust to arrest the slowdown
b. Increasing thrust to accelerate to airspeed above L/DMax speed
c. Increasing thrust to maximum available thrust and reducing bank angle while
accelerating to airspeed above L/DMax speed. In a thrust limited situation, exiting
slow flight will require an immediate descent as an aerodynamic stall is imminent. - ANSWER-c. Increasing thrust to maximum available thrust and reducing bank angle while
accelerating to airspeed above L/DMax speed. In a thrust limited situation, exiting
slow flight will require an immediate descent as an aerodynamic stall is imminent.
Maximum Altitude is the highest altitude at which an airplane can be operated.
Maximum Altitude for an airplane is:
a. Maximum Certified Altitude - The altitude determined during certification set by
the pressurization structural load limits on the fuselage.
b. Thrust Limited Altitude - The altitude at which sufficient thrust is available to
provide a specific minimum rate of climb.
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