If the Angle of Attack and other factors remain constant, and the airspeed is doubled, lift will be:

03 Aerofoils and Lift Drag

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Professional Development
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Hard
Thiago Lopes
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20 questions
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1.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
Doubled.
One quarter of what it was.
The same.
Quadrupled.
2.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
The definition of lift is:
The aerodynamic force which acts perpendicular to the chord line of the aerofoil.
The aerodynamic force that results from the pressure differentials about an aerofoil.
The aerodynamic force which acts perpendicular to the upper surface of the aerofoil.
The aerodynamic force which acts at 90° to the relative airflow.
3.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
Resistance, or skin friction, due to the viscosity of the air as it passes along the surface of a wing, is a type of:
Induced drag.
Form drag.
Parasite drag.
Interference drag.
4.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
As airspeed increases induced drag _____, parasite drag _____, and total drag _____:
Increases, Increases, Increases
Increases, Decreases, Increases then decreases
Decreases, Decreases, Decreases
Decreases, Increases, Decreases then increases
5.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
The maximum value of the coefficient of lift is found at an angle of attack of approximately:
Minus 4 degrees.
0 degrees.
4 to 6 degrees.
16 degrees.
6.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
An aerofoil section is designed to produce lift resulting from a difference in the:
Negative air pressure below and a vacuum above the surface.
Higher air pressure below the surface and lower air pressure above the surface.
Vacuum below the surface and greater air pressure above the surface.
Higher air pressure at the leading edge than at the trailing edge.
7.
MULTIPLE CHOICE QUESTION
45 sec • 1 pt
At a given Indicated Air Speed, what effect will an increase in air density have on lift and drag?
Lift will increase but drag will decrease.
Lift and drag will increase.
Lift and drag will decrease.
Lift and drag will remain the same.
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