Hostname: page-component-cd9895bd7-7cvxr Total loading time: 0 Render date: 2025-01-05T11:43:16.582Z Has data issue: false hasContentIssue false
  • English
  • Français

An Experimental Investigation of Base Flows at Supersonic Speeds

Published online by Cambridge University Press:  04 July 2016

M. A. Badrinarayanan
M. A. Badrinarayanan*
Affiliation:
Department of Aeronautical Engineering, Indian Institute of Science, Bangalore
Get access Rights & Permissions [Opens in a new window]

Summary

Detailed measurements in the wake flow behind blunt based two-dimensional and three-dimensional bodies have been made at M = 2. The results throw some light on the behaviour of separated flows and indicate the importance of flow reversal. The results for the two-dimensional body are in agreement with the Crocco and Lees’ theory on separated shear flows. A preliminary study of the effect of air injection at the base shows that the base pressures increase significantly.

Type
Research Article
Information
The Aeronautical Journal , Volume 65 , Issue 607 , July 1961 , pp. 475 - 482
Copyright
Copyright © Royal Aeronautical Society 1989

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.Chapman, D. R. (1951). An Analysis of Base Pressure at Supersonic Velocities and Comparison with Experiment. N.A.C.A. Report 1051, 1951.Google Scholar
2.Bogdonoff, S. M. (1952). A Preliminary Study of Reynolds Number Effects on Base Pressure at M = 2-95. Journal of the Aeronautical Sciences, Vol. 19, No. 3, 1952.Google Scholar
3.Kurzweg, H. H. (1951). Inter-relationship Between Boundary Layer and Base Pressure. Journal of the Aeronautical Sciences, Vol. 18, No. 11, 1951.CrossRefGoogle Scholar
4.Gadd, G. E., Holder, D. W. and Regan, J. D. (1956). Base Pressures in Supersonic Flow. C.P. No. 271, A.R.C. Technical Report, 1956.Google Scholar
5.Crocco, L. and Lees, L. (1952). A Mixing Theory for Interaction Between Dissipative Flows and Nearly Isentropic Streams. Journal of the Aeronautical Sciences, Vol. 19, No. 10, 1952.Google Scholar
6.Dhawan, S. (1955). Design and Operation of an Intermittent 1 in. x 3 in. Supersonic Wind Tunnel. Journal of the Aeronautical Society of India, Vol. 7, No. 1, 1955.Google Scholar