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Measured Pressure Distributions and Shock Shapes on a Simple Delta Wing

Published online by Cambridge University Press:  07 June 2016

L.C. Squire
L.C. Squire*
Affiliation:
Cambridge University Engineering Department
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Summary

This note presents the results of an experimental investigation of the flow over a simple delta wing designed for a Mach number of 3.5. Complete pressure distributions were measured for incidences of 0°, 10° and 20° at Mach numbers of 2.5 and 3.5. A number of schlieren photographs of the shock system around the wing were obtained at the same conditions and surface streamline patterns were studied at M = 3.5. The measurements were made to support numerical calculations which use this wing as a test case.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 32 , Issue 3 , August 1981 , pp. 188 - 198
Copyright
Copyright © Royal Aeronautical Society. 1981

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References

1 Butler, D.S. The numerical solution of hyperbolic systems of partial differential equations in three independent variables. Proc. Roy. Soc. 255, pp 232–252, 1960.Google Scholar
2 Hillier, R. Pressure distributions at M = 3.51 and at high incidence on four delta planform. Aero Res. Counc. Current Paper 1198, 1972.Google Scholar
3 Narayan, K.Y. Pressure distributions on two wings with curved leading edges at supersonic speeds. Aero Res. Counc. R & M 3741, 1974.Google Scholar
4 Pate, S.R. Measurements and correlations of transition Reynolds number on sharp slender cones at high speeds. AIM Journal, 9, pp 1082–1090, 1971.Google Scholar