The velocity of the air just over the wing is (in m/s):
250
125
500
200
A
125
B
500
C
250
D
200
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Solution
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Compression of the streamlines means that the stream tube above the wing has a smaller cross-sectional area than that in front of the plane and from the continuity equation , the velocity v' of the air must therefore be greater above the wing. Area A′=810A
⇒AA′=108 From continuity equation: Av=A′v′ ∴v′=AA′v=108×200=250ms−1
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