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Basic Aerodynamics Questions
by
Ridhima kapoor
November 1, 2016
8,064
views
53
plays
1
A delta wing has
a higher stall angle than a straight wing
a lower stall angle than a straight wing
the same stall angle than a straight wing
2
The Lift/Drag ratio of a wing at the stalling angle is
of a negative value
low
high
3
The airflow over the upper surface of a cambered wing
increases in velocity and pressure
increases in velocity and reduces in pressure
reduces in velocity and increases in pressure
4
The speed of air over a swept wing which contributes to the lift is
less than the aircraft speed
more than the aircraft speed
the same as the aircraft speed
5
In straight and level flight, the angle of attack of a swept wing is
the same as the aircraft angle to the horizontal
more than the aircraft angle to the horizontal
less than the aircraft angle to the horizontal
6
Induced drag
is never equal to the profile drag
is equal to the profile drag at the stalling speed
is equal to the profile drag at Vmd
7
A delta wing aircraft flying at the same speed (subsonic) and angle of attack as a swept wing aircraft of similar wing area will produce
the same lift
more lift
less lift
8
The stagnation point is
static pressure plus dynamic pressure
static pressure minus dynamic pressure
dynamic pressure only
9
If a swept wing stalls at the tips first, the aircraft will
pitch nose up
pitch nose down
roll
10
The thickness/chord ratio of the wing is also known as
aspect ratio
mean chord ratio
fineness ratio
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