Hostname: page-component-78c5997874-8bhkd Total loading time: 0 Render date: 2024-11-09T16:18:02.275Z Has data issue: false hasContentIssue false
  • English
  • Français

The Pressure on Flat and Anhedral Delta Wings with Attached Shock Waves

Published online by Cambridge University Press:  07 June 2016

J Pike
J Pike*
Affiliation:
Royal Aircraft Establishment, Bedford
Get access

Summary

An expression is derived which relates the pressure on a wing in a supersonic free stream to the pressure on a thin wing with the same surface shape. The expression is used to find the pressure distribution for caret wings and flat delta wings with attached flow at their leading edges. The compression surface pressure distributions found are in good agreement with existing experimental and theoretical results, except when large pressure changes occur in the flow behind the attached shock wave. Some expansion surface results are also obtained for wings with an isentropic expansion at the leading edge. The effects of flow and geometry changes on the pressure distribution are investigated. It is found that a small improvement in the lift/drag ratio of a caret wing can be obtained by halving the anhedral required for the plane shock wave condition.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 4 , November 1972 , pp. 253 - 262
Copyright
Copyright © Royal Aeronautical Society. 1972

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. Nonweiler, T Delta wings of shapes amenable to exact shock-wave theory. ARC 22 644, March 1961.Google Scholar
2. Snow, R M Aerodynamics of thin quadrilateral wings at supersonic speeds. Quarterly of Applied Mathematics, Vol V, No 4, 1947.Google Scholar
3. Chernyi, G G Introduction to Hypersonic Flow. Academic Press, 1961.Google Scholar
4. NASA-Ames Research Staff Equations, tables and charts for compressible flow. NASA Report 1135, 1953.Google Scholar
5. South, J C Jnr, Klunker, E B Methods for calculating non-linear conical flows. NASA SP-228, 1969.Google Scholar
6. Voskresenskii, G P Numerical solution of the problem of a supersonic gas flow past an arbitrary surface of a delta wing in the compression region. Izv Akad Nauk SSSR, Mekh Zhid 1, Gaya 4, 1968.Google Scholar
7. Babaev, D A Numerical solution of the problem of supersonic flow past the lower surface of a delta wing. AIAA Journal, Vol 1, September 1963.Google Scholar
8. Squire, L C Pressure distributions and flow patterns at M = 4.0 on some delta wings. ARC R&M 3373, 1964.Google Scholar
9. Squire, L C Calculated pressure distributions and shock shapes on conical wings with attached shock waves. Aeronautical Quarterly, Vol XIX, pp 31-50, February 1968.Google Scholar
10. Roe, P L A special off-design flow for caret wings. Private communication.Google Scholar
11. Pike, J The flow past flat and anhedral delta wings with attached shock waves. RAE Technical Report 71081, April 1971.Google Scholar
12. Pike, J Theoretical pressure distributions on four simple wing shapes for a range of supersonic flow conditions. RAE Technical Report 71064, March 1971.Google Scholar
13. Lomax, H Kutler, P Numerical solutions for the complete shock wave structure behind supersonic-edge delta wings. Third Conference on Sonic Boom Research. NASA, Washington DC, October 29-30, 1970.Google Scholar
14. Mead, R M Kock, F Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock. Grumman Aircraft Engineering Corporation, ASD TR 61-60, May 1962.Google Scholar