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A Note on Supersonic Wing Integral Equations in Unsteady Flow*
Published online by Cambridge University Press: 07 June 2016
Summary
The integral equations for the pressure distribution on an oscillating thin wing having a prescribed velocity distribution in a supersonic flow are developed.
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- Research Article
- Information
- Copyright
- Copyright © Royal Aeronautical Society. 1952
Footnotes
This work was done in 1948, at which time it was hoped to extend the very elegant methods available for the steady flow problem. All attempts to generalise these methods for wings of arbitrary plan form having proved nugatory, it is felt that the integral equations are worth recording.
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