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Supersonic Flow Past a Slender Delta Wing. An Experimental Investigation Covering the Incidence Range –5° ≤ α ≤ 50°

Published online by Cambridge University Press:  07 June 2016

I C Richards
I C Richards*
Affiliation:
Cranfield Institute of Technology
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Summary

A detailed survey of a delta wing of 70° sweep has been performed at M = 2.5. The measurements include upper- and lower-surface pressure distributions, schlieren photographs, vapour-screen photographs and surface oil-flow visualisation. The results have been compared with thin-shock-layer theory and various other predictions.

Type
Research Article
Information
Aeronautical Quarterly , Volume 27 , Issue 2 , May 1976 , pp. 143 - 153
Copyright
Copyright © Royal Aeronautical Society. 1976

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References

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