Hostname: page-component-848d4c4894-sjtt6 Total loading time: 0 Render date: 2024-06-24T10:03:14.286Z Has data issue: false hasContentIssue false
  • English
  • Français

Large amplitude oscillation effects on cone pitch stability in viscous hypersonic flow

Published online by Cambridge University Press:  04 July 2016

G. R. Hutt ,
R. A. East  and
R. D. Wilson
G. R. Hutt
Affiliation:
Department of AeronauticsandAstronautics University of Southampton
R. A. East
Affiliation:
Department of AeronauticsandAstronautics University of Southampton
R. D. Wilson
Affiliation:
Department of AeronauticsandAstronautics University of Southampton
Get access Rights & Permissions [Opens in a new window]

Summary

Experimental and theoretical, small and large amplitude stability data are presented for a pointed and a 0.2 bluntness ratio, 10° semi-angle cone performing pitching oscillations in hypersonic flow at a Mach number of 6.85. Analysis identifies that large amplitude model motion time histories cannot be predicted from a knowledge of small amplitude oscillation stability derivatives data. At the Reynolds numbers of the experiments the pointed and blunted cone are subject to significant hypersonic flow viscous phenomena, which are proposed as the cause of the small to large amplitude stability prediction being invalid.

Type
Research Article
Information
The Aeronautical Journal , Volume 93 , Issue 922 , February 1989 , pp. 50 - 57
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. Uselton, J. C. and Uselton, B. L. Validity of small amplitude oscillation dynamic stabilitv measurement technique. J Spacecraft Rockets, May 1976. 13, (5), 266–270.Google Scholar
2. Ericsson, L. E. Unsteady embedded Newtonian flow. Astronaut Acta, 1973, 18, 309–330.Google Scholar
3. East, R. A. and Qasrawi, A. M. S. A Long Stroke Isentropic Free Piston Hypersonic Wind Tunnel. Aeronautical Research Council. ARC R & M No. 3844. Aug. 1978.Google Scholar
4. East, R. A. Non-Linear Hypersonic Static and Dynamic Stability of Axisymmetric Shapes. EuroMech Colloquium No. 126. Berlin, April 1980.Google Scholar
5. Ericsson, L. E. Non-linear hypersonic viscous crossflow effects on slender vehicle dynamics.AIAA J, June 1979, 17, (6), 586–593.Google Scholar
6. Seiff, A. Secondary Flowfields Embedded in Hypersonic Shock Layers. NASA TN-D-1304. May 1962.Google Scholar
7. Ericsson, L. E. Modifications of Aerodynamic Predictions of the Longitudinal Dynamics of Tactical Weapons. Lockheed Missiles and Space Company Inc., LMSC D-646354, 1976.Google Scholar
8. East, R. A. and Hutt, G. R. Hypersonic static and dynamic stability of axisymmetric shapes - a comparison of prediction methods and experiment. AGARD Conference Proceedings No. 428, Aerodynamics of hypersonic lifting vehicles, 1987.Google Scholar
9. Hull, G. R. and East, R.A. Optical techniques for model position measurement in dynamic wind tunnel testing, Meets Control, 1985, 18, (3), 99–101.Google Scholar
10. East, R. A., Qasrawi, A. M. S. and Khalid, M. An experimental study of the hypersonic dynamic stability of pitching blunt conical and hyperballistic shapes in a short running time facility, AGARD Conference Proceedings No. 235, Dynamic Stability Parameters, 1978.Google Scholar
11. Ward, L. K. Influence of Boundary Layer Transition on Dynamic Stability at Hypersonic Speeds, Paper No. 6 Transactions of the 2nd Technical Workshop on Dynamic Stability Testing. Arnold Air Force Station, Tennessee, 1965.Google Scholar
12. Ericsson, L. E. Transition effects on slender cone pitch damping, J Spacecraft Rockets, 1988, 25, (1). 4–8.Google Scholar
13. Softley, E. J., Graber, E. C. and Zempel, R. C. Experimental observations of transition of the hypersonic boundary layer, AIAA J, 1969, 7, (2). 257–263.Google Scholar
14. Adams, J. C. Jnr and Griffith, B. J. Hypersonic viscous static stability of a sharp 5 deg cone at incidence, AIAA J, 1976. 14, 1062–1068.Google Scholar
15. Miller, C. G. and Gnoffo, P. A., An Experimental Investigation of Hypersonic Flow over Biconics at Incidence and Comparison to Prediction, AIAA Paper No. 82-1382, 1982.Google Scholar
16. Stetson, K. F. Boundary layer separation on slender cones at angle of attack, AIAA J 1972, 10, (5), 642–648.Google Scholar
17. Hill, W. H. and Tobak. M., Bifurcation analysis of aircraft pitching motions about large mean angles of attack. J Guidance Control, January 1984, 7, (1), 113–121.Google Scholar
18. Hui, W. H. and Van Roessel, H. J. Transient Motion of Hypersonic Vehicles including Time History Effects. AIAA Paper 85-0201, January 1985.Google Scholar
19. Tobak, M and Schiff, L. E. The role of time history effects in the formulation of the aerodynamics of aircraft dynamics. AGARD Conference Proceedings No. 235. Dynamic Stability Parameters, Paper 26, 1978.Google Scholar
20. Khalid, M. A Theoretical and Experimental Study of the Hypersonic Dynamic Stability of Blunt Axisymmetric Conical and Power-Law Shaped Bodies. Ph.D. Thesis, Department of Aeronautics and Astronautics, University of Southampton, 1977.Google Scholar
21. Rie, H., Linkiewics, E. A. and Bosworih, F. D. Hypersonic Dynamic Stability Part III, Unsteady Flowfield Program, FDC- TDR-64-149, 1967.Google Scholar