Hostname: page-component-848d4c4894-xfwgj Total loading time: 0 Render date: 2024-06-17T11:12:02.887Z Has data issue: false hasContentIssue false
  • English
  • Français

Flow Regimes over Delta Wings at Supersonic and Hypersonic Speeds

Published online by Cambridge University Press:  07 June 2016

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

Summary

This paper concerns the boundaries between flow regimes for sharp-edged delta wings in supersonic flow and the relation of some predictions of thin-shock-layer theory to these boundaries. In particular, it is shown that the theory predicts that the attachment lines on the lower surface of a thin delta wing at supersonic speeds suddenly jump from just inboard of the leading edges to the centre line in certain flight conditions. In general there is close agreement between the conditions for this jump and the flight conditions corresponding to the change-over from attached flow to the leading-edge separation on the upper surface. Since the movement of the attachment lines on the lower surface must change the position of the sonic line and the nature of the expansion around the edge, it is suggested that the two phenomena are directly related. Thus thin-shock-layer theory can be used to establish the boundaries of the various flow regimes for a wide range of Mach number, incidence and wing sweep. The theory can also be used to predict the effects of wing thickness on leading-edge separation, but here the experimental data is very sparse and somewhat contradictory, so the value of the prediction in the case of thickness requires further investigation.

Type
Research Article
Information
Aeronautical Quarterly , Volume 27 , Issue 1 , February 1976 , pp. 1 - 14
Copyright
Copyright © Royal Aeronautical Society. 1976

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 Squire, L C The characteristics of some slender cambered gothic wings at Mach numbers from 0.4 to 2.0. R&M 3370, 1964.Google Scholar
2 Stanbrook, A Squire, L C Possible types of flow at swept leading edges. Aeronautical Quarterly, Vol XV, pp 72–82, 1964.Google Scholar
3 Whitehead, A H Hefner, J N Rao, D M Lee-surface vortex effects over configurations in hypersonic flow. AIAA Paper 72-77, 1972.Google Scholar
4 Squire, L C Jones, J G Stanbrook, A An experimental investigation of the characteristics of some plane and cambered 65° delta wings at Mach numbers from 0.7 to 2.0. R&M 3305, 1961.Google Scholar
5 Rein, J A Flow over the suction surface of sharp-edge delta wings with detached leading-edge shock waves. Australian Weapons Research Laboratories, TN HSA 102, 1964.Google Scholar
6 Cross, E J Hankey, W L Investigation of the leeward side of a delta wing at hypersonic speeds. Journal of Spacecraft, Vol 6, pp 185–190, 1969.CrossRefGoogle Scholar
7 Reding, J P Ericsson, L E Review of delta wing space shuttle vehicle dynamics. Paper 30 in NASA TM X-2508, 1971.Google Scholar
8 Messiter, A F Lift of slender delta wings according to Newtonian theory. AIAA Journal, Vol 1, pp 794–801, 1963.CrossRefGoogle Scholar
9 Shanbhag, V V Numerical studies on hypersonic delta wings with detached shock waves. ARC Current Paper 1277, 1974.Google Scholar
10 Squire, L C Some extensions of thin-shock-layer theory. Aeronautical Quarterly, Vol XXV, pp 1–13, 1974.Google Scholar
11 Squire, L C Calculated pressure distributions and shock shapes on thick conical wings at high supersonic speeds. Aeronautical Quarterly, Vol XVIII, p 185, 1967.Google Scholar
12 Bazzhin, A P Calculation of flow past plane triangular wings at large angles of attack. Izv AN SSSR Mekhanika Zhidkosti i Gaza, Vol 1, pp 104–105, 1966.Google Scholar
13 Bashkin, V A Experimental study of flow about flat delta wings at M = 5 and angles of attack from 0 to 70°. Izv AN SSSR Mekhanika Zhidkosti i Gaza, Vol 2, No 3, pp 102–108, 1967.Google Scholar
14 Michael, W H Flow studies on flat-plate delta wings at supersonic speeds. NACA TN 3472, 1955.Google Scholar
15 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. ARC Current Paper 1131, 1969.Google Scholar
16 Thomann, H Measurements of heat transfer, recovery temperature, and pressure distribution on delta wings at M = 3. FFA (Sweden) Report 93, 1963.Google Scholar