Hostname: page-component-84b7d79bbc-fnpn6 Total loading time: 0 Render date: 2024-08-05T06:08:48.585Z Has data issue: false hasContentIssue false
  • English
  • Français

Experimental investigation of the supersonic flow past a slender cone at high incidence

Published online by Cambridge University Press:  12 April 2006

C. Nebbeling  and
W. J. Bannink
C. Nebbeling
Affiliation:
Department of Aerospace Engineering, University of Technology, Delft, The Netherlands
W. J. Bannink
Affiliation:
Department of Aerospace Engineering, University of Technology, Delft, The Netherlands
Get access Rights & Permissions [Opens in a new window]

Abstract

The supersonic flow field past a circular cone of semi-apex angle 7·5° at incidences up to 26° has been investigated experimentally at a free-stream Mach number of 2·94. The experiments were made using a five-hole conical-head directional probe. Since the flow past the cone was found to be conical, the flow phenomena may be described in a plane perpendicular to the cone axis. This paper gives the direction of the conical streamlines, the conical sonic line and the conical Mach number in such a plane, all of which may be deduced from the measurements. At incidences exceeding twice the cone semi-apex angle a separated flow regime was observed which consisted of two main vortices on either side of the leeward plane of symmetry, and probably also two secondary vortices close to the cone surface. From incidences of 17° onwards, an embedded region of conical supersonic flow terminated by a shock wave was revealed. At 22°, approximately, a second embedded shock wave was measured close to the cone surface and extended slightly across the leeward plane of symmetry. This shock wave may have been generated by the vortex system, which induced supersonic cross-flow components towards the cone.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 87 , Issue 3 , 15 August 1978 , pp. 475 - 496
Copyright
© 1978 Cambridge University Press

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

Andrews, D. R. & Sawyer, W. G. 1963 Aero. Res. Counc. Current Paper no. 628.
Bakker, P. G. & Bannink, W. J. 1974 Dept. Aerospace Engng, Delft Univ. Tech., Rep. VTH-184.
Bontoux, P. & Roux, B. 1975 A.I.A.A. Paper no. 75–858.
Feldhuhn, R. H. & Winkelmann, A. E. 1969 Naval Ordnance Lab., White Oak, Md, Rep. NOL-TR-69-36.
Feldhuhn, R. H., Winkelmann, A. E. & Pasiuk, L. 1970 A.I.A.A. Paper no. 70–766.
Fletcher, C. A. J. 1975 Proc. 4th Int. Conf. Num. Meth. Fluid Dyn. Lecture Notes in Physics, vol. 35, pp. 161–166. Springer.
Guffroy, D., Roux, B., Marcillat, J., Brun, R. & Valensi, J. 1968 Agard Conf. Proc. no. 30, paper 20.
Holt, M. & Ndefo, D. E. 1970 J. Comp. Phys. 5, 463–486.
Houwink, R. 1974 Dept. Aerospace Engng., Delft Univ. Tech., Rep. VTH-168.
Houwink, R. & Nebbeling, C. 1975 Delft Prog. Rep. C 1, 69–76.
Jones, D. J. 1969 AGARDograph no. 137.
Kutler, P. & Lomax, H. 1971 A.I.A.A. Paper no. 71–99.
Lubard, S. C. & Helliwell, W. S. 1973 A.I.A.A. Paper no. 73–636.
Massot, P. 1976 Thèse de doctorat, Université d'Aix-Marseille.
Nakao, S. I. 1975 Inst. Space Aero. Sci., Univ. Tokyo, Rep. no. 534.
Rainbird, W. J. 1968 AGARD Conf. Proc. no. 30, paper 19.
Stetson, K. F. 1972 A.I.A.A. J. 10, 642–648.
Tracy, R. R. 1963 Aero. Lab., Cal. Inst. Tech., Memo. no. 69.
Yahalom, R. 1971 Aero. Sci. Div., Univ. California, Berkeley, Rep. AFOSR-TR-71-2183.
Zakkay, V. & Alzner, E. 1974 Air Force Flight Dyn. Lab., Wright-Patterson AFB, Ohio, Rep. AFFDL-TR-74-19.