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Calculation of Downwash Behind a Supersonic Wing
Published online by Cambridge University Press: 07 June 2016
Extract
Once the linearised lift problem for a supersonic wing has been solved and the disturbance velocity potential or the pressure is known at every point on the surface, the complete flow round the wing and the downwash behind the wing may be found by the following procedure.
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- Copyright © Royal Aeronautical Society. 1949
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