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High Mach number dynamic stability of blunt slender cones at angle of attack

Published online by Cambridge University Press:  04 July 2016

M. Khalid
M. Khalid*
Affiliation:
National Research Council Canada
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Abstract

The dynamic stability of blunt cones at angles of attack and high supersonic Mach numbers has been investigated along lines similar to the pointed cone solution derived by the present author. The steady pressure distribution on a blunt cone is complemented with a first and second order azimuth contribution resulting from an angle of. attack displacement. The unsteady perturbation is then superimposed on the steady solution by accounting for the streamline deflection in an oscillating flow. The closed form expressions obtained for the dynamic stability of blunt cones reduce to their pointed cone counterparts once the bluntness parameter is equated to zero. The comparison between the theoretical and measured results is quite encouraging.

Type
Technical Note
Information
The Aeronautical Journal , Volume 96 , Issue 959 , November 1992 , pp. 356 - 359
Copyright
Copyright © Royal Aeronautical Society 1992 

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References

1. Khalid, M. and East, R.A. High Mach number dynamic stability of pointed cones at small angles of attack, AIAA J, October 1980, 18.Google Scholar
2. Eggers, AJ. and Savin, R.C. Approximate methods for calculating the flow about non-lifting bodies of revolution at high supersonic airspeeds, NACA TN-2579, 1951.Google Scholar
3. Eggers, A J. On the calculation of flow about objects travelling at high supersonic speeds, NACA TN-2811, 1952.Google Scholar
4. Scott, C.J. A Theoretical and Experimental Determination of the Pitching Derivative of Cones in Hypersonic Flow, MSC Thesis, AASU Report, No. 67, University of Southampton, 1967.Google Scholar
5. Krasnov, N. F. Aerodynamics of bodies of revolution, pp. 621-625. Edited and annotated by Deane, N. M. American Elsevier Publishing, N.Y. 1970.Google Scholar
6. Kopal, Z. Tables of Supersonic Flow around cones at Large Yaw, MIT TR No. 5, 1949.Google Scholar
7. Chernyi, G.G. Introduction to hypersonic flow, translated and edited by Probstein, Ronald F.. Academic Press New York and London, 1961.Google Scholar
8. Khalid, M. and East, R.A. Stability derivative of blunt cones at high Mach number, Aero Q, November 1979, 30, pp 559–590.Google Scholar
9. Khalid, M. A Theoretical and Experimental Study of the Hypersonic Dynamic Stability of Blunt, Axisymmetric Conical and Power Law Shapes, PhD Thesis, University of Southampton, England, 1977.Google Scholar
10. East, R.A. and Hutt, G.R. Hypersonic static and dynamic stability of axisymmetric shapes — a comparison of prediction methods and experiment, AGARD Symposium on Aerodynamics of Hypersonic Lifting Vehicles, April 1987.Google Scholar
11. East, R.A., Quasrawi, A.M. and Khalid, M., An experimental study of hypersonic shapes in a short running time facility, AGARD Conference Proceedings, No. 235, November 1978.Google Scholar
12. Fink, M R., Carrole, J.B. and Owen, F.S., Calculation of hypersonic dynamic stability, United Aircraft Corporation Research Laboratories, AD 442 280, June 1964.Google Scholar