Hostname: page-component-848d4c4894-2pzkn Total loading time: 0 Render date: 2024-05-20T23:31:51.251Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access

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

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1 Narayan, K Yegna, Pressure distributions on two wings with curved leading edges at supersonic speeds. ARC R & M 3741, 1974.Google Scholar
2 Hillier, R, The effects of yaw on conical wings at high supersonic speeds. Aeronautical Quarterly, Vol XXI, p 199, 1970.CrossRefGoogle Scholar
3 Messiter, A F, Lift of slender delta wings according to Newtonian Theory. AIAA Journal, Vol 1, p 794, 1963.Google Scholar
4 Hida, K, Thickness effects on the force of slender delta wings in hypersonic flow. AIAA Journal, Vol 3, p 427, 1965.Google Scholar
5 Squire, L C, Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol XXVIII, p 185, 1967.Google Scholar
6 Shanbhag, V V, Numerical studies on hypersonic delta wings with detached shock waves. ARC Current Paper 1277, 1974.Google Scholar
7 Hayes, W D, Probstein, R F, Hypersonic Flow Theory, Academic Press, New York, 1966.Google Scholar