Hostname: page-component-5c6d5d7d68-sv6ng Total loading time: 0 Render date: 2024-08-16T17:55:51.699Z Has data issue: false hasContentIssue false
  • English
  • Français

The Effects of Yaw on Conical Wings at High Supersonic Speeds

Published online by Cambridge University Press:  07 June 2016

R. Hillier
R. Hillier*
Affiliation:
Cambridge University, Engineering Department
Get access

Summary

In recent papers Squire has presented results for the shock shape and pressure distribution on the lower surface of unyawed, lifing, conical bodies with sharp leading edges. The work, a development of Messiter’s first-order correction to Newtonian theory, was successfully applied to wings of diamond and caret section. This paper shows how the method may be used to include the effects of yaw. Results are presented here for the flat wing and some biconvex sections. Comparisons are made with experiment for both the flat and biconvex wings and agreement is shown to be good.

Type
Research Article
Information
Aeronautical Quarterly , Volume 21 , Issue 3 , August 1970 , pp. 199 - 210
Copyright
Copyright © Royal Aeronautical Society. 1970

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. Messiter, A. F. Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol. 1, p. 794, 1963.Google Scholar
2. Squire, L. C. Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol. XVIII, p. 185, 1967.CrossRefGoogle Scholar
3. Squire, L. C. Calculated pressure distributions and shock shapes on conical wings with attached shock waves. Aeronautical Quarterly, Vol. XIX, p. 31, 1968.CrossRefGoogle Scholar
4. Hida, K. Thickness effect on the force of slender delta wings in hypersonic flow. AIAA Journal, Vol. 3, p. 427, 1965.CrossRefGoogle Scholar
5. Squire, L. C. Calculation of pressure distributions on lifting conical wings with application to the off-design behaviour of wave riders. AGARD Conference Proceedings 30, May 1968.Google Scholar
6. Larcombe, M. J. An investigation of the flow around a delta wing with triangular cross-sections at a Mach number of 4·0. Being published.Google Scholar
7. Squire, L. C. Pressure distributions and some flow patterns on some conical shapes with sharp leading edges and symmetrical sections at M =4·0. ARC R & M 3340, 1963.Google Scholar