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Supersonic flow and wing-body interference
Published online by Cambridge University Press: 26 February 2010
Summary
The velocity potential near the boundary of the disturbance is determined for steady supersonic flow past a simple body-and-wing model. It is found that the disturbance decays exponentially as it spreads round the body; the alteration caused by changing the radius of curvature is discussed. A universal formula for the potential away from the fuselage is also derived.
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- Copyright © University College London 1967
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