Hostname: page-component-7b7567c8c-7pwfn Total loading time: 0 Render date: 2026-11-13T11:29:54.214Z Has data issue: false hasContentIssue false
  • English
  • Français

Some Extensions of Thin-Shock-Layer Theory

Published online by Cambridge University Press:  07 June 2016

L C Squire
L C Squire*
Affiliation:
Cambridge University, Engineering Department
Get access

Summary

In the usual form of thin-shock-layer theory it is assumed that the flow about a lifting body can be expanded in terms of the inverse density ratio across a basic oblique shock wave lying in the plane of the leading edges of the body. In this paper it is shown that more accurate results can be obtained by moving the basic shock closer to the calculated shock wave below the body. The results obtained show why the original form of thin-shock-layer theory often gave good agreement with experiment in conditions which appeared to be outside the range of validity of the theory.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 25 , Issue 1 , February 1974, pp. 1 - 13
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.)

Article purchase

Temporarily unavailable

References

1 Messiter, A F, Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol 1, p 794,1963.CrossRefGoogle Scholar
2 Hida, K, Thickness effects on the force of slender delta wings in hypersonic flow. AIAA Journal, Vol 3, p 427, 1965.CrossRefGoogle Scholar
3 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
4 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
5 Squire, L C, Calculations of the pressure distribution on lifting conical wings with applications to the off-design behaviour of wave riders. Paper 11 in AGARD Conference Proceedings 30, 1968.Google Scholar
6 Roe, P L, A simple treatment of the attached shock layer on a delta wing. RAE Technical Note 70 246, 1970.Google Scholar
7 Woods, B A, Hypersonic flow with attached shock waves over delta wings. Aeronautical Quarterly, Vol XXI, p 379, 1970.CrossRefGoogle Scholar
8 Hillier, R, The effects of yaw on conical wings at high supersonic speeds. Aeronautical Quarterly, Vol XXI, p 199, 1970.CrossRefGoogle Scholar
9 Shanbhag, V V, Numerical studies on hypersonic delta wings with detached shock waves. To be published in ARC Current Paper series.Google Scholar
10 Hillier, R, Three-dimensional wings in hypersonic flow. Journal of Fluid Mechanics, Vol 54, p 305, 1972.CrossRefGoogle Scholar
11 Hui, W H, Supersonic and hypersonic flow with attached shock waves over delta wings. Proc Roy Soc A, Vol 1325, p 250, 1971.Google Scholar
12 Hui, W H, Effect of yaw on supersonic and hypersonic flow over delta wings. Aeronautical Journal, Vol 77, p 299, 1973.CrossRefGoogle Scholar
13 Hui, W H, The caret wing at certain off-design conditions. Aeronautical Quarterly, Vol XXIII, p 263, 1972.CrossRefGoogle Scholar
14 Pike, J, The pressure on flat and anhedral delta wings with attached shock waves. Aeronautical Quarterly, Vol XXIII, p 253, 1972.CrossRefGoogle Scholar
15 Peckham, D H, Pressure distribution measurements on a series of slender body shapes at Mach numbers of 6.85 and 8.60. ARC Current Paper 791, 1962.Google Scholar
16 Squire, L C, Pressure distributions and flow patterns at M = 4.0 on some delta wings. ARC R & M 3373,1963.Google Scholar
17 Fellows, K A, Carter, E C, Results and analysis of pressure measurements on two isolated slender wings and slender wing-body combinations at supersonic speeds. Aircraft Research Association Report 12, 1969.Google Scholar
18 Squire, L C, Pressure distributions and flow patterns on some conical shapes with sharp leading edges at M = 4.0. ARC R & M 3340, 1962.Google Scholar