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The Transonic Aerofoil Problem with Embedded Shocks

Published online by Cambridge University Press:  07 June 2016

Helge Nørstrud
Helge Nørstrud*
Affiliation:
Lockheed-Georgia Company
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Summary

The integral equation approach to the mixed flow problem of infinite wings at high subsonic speeds is adopted for non-circulatory and circulatory (lifting) flows. The solutions are determined from a system of non-linear algebraic equations and, to ensure always unique solutions, the method of differentiation with respect to a parameter has been applied. The resulting Cauchy problem is then solved with the linearised flow solution as the initial value vector. For the case of embedded shocks in the flow field, the method of steepest descent has been added to the calculation scheme. Results for subcritical and supercritical flows past aerofoils are given and compared with solutions obtained by finite-difference techniques.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 24 , Issue 2 , May 1973, pp. 129 - 138
Copyright
Copyright © Royal Aeronautical Society. 1973

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References

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