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Effects of Yaw on a Gothic Wing at Supersonic Speeds

Published online by Cambridge University Press:  07 June 2016

K Yegna Narayan
K Yegna Narayan*
Affiliation:
Cambridge University, Engineering Department
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Summary

Results are presented of an experimental study of the pressures on the flat windward surface of a Gothic wing at a free-stream Mach number of 3.5 and at moderately high angles of attack, including the effects of yaw. The results show that the perturbation in pressure due to yaw is almost independent of the streamwise distance from the vertex. As a result, it has been possible to calculate the pressure distribution on the yawed wing using the appropriate yawed conical wing results, the zero yaw results being calculated by the “equivalent” delta wing method. The calculations show reasonable agreement with the experiments and confirm that the perturbation due to yaw generates a stabilising rolling moment.

Type
Research Article
Information
Aeronautical Quarterly , Volume 25 , Issue 2 , May 1974 , pp. 119 - 128
Copyright
Copyright © Royal Aeronautical Society. 1974

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References

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