Hostname: page-component-54dcc4c588-sq2k7 Total loading time: 0 Render date: 2025-09-19T01:41:41.217Z Has data issue: false hasContentIssue false
  • English
  • Français

Viscous contribution to the high Machnumber damping in pitch of blunt slender cones atsmall angles of attack

Published online by Cambridge University Press:  04 July 2016

M. Khalid
M. Khalid*
Affiliation:
Institute for Aerospace Research, National Research Council of Canada
Get access Rights & Permissions [Opens in a new window]

Summary

The dynamic stability derivatives of blunt cones forsmall variations in angles of attack have beenpreviously derived by the current author. However,no account of the unsteady nature of the boundarylayer was made in that work. In this paper closedform expressions for the increment in dynamicstability due to the presence of the boundary layerare derived by considering the pressure distributionperturbations as the boundary layer continuouslyadjusts to the enclosed oscillating body. The theoryprovides a first hand estimate of the complete pitchderivative damping without having to resort to morerigorous and expensive computational methods.Calculations performed at Mach numbers of 7 to 10with axis positions ranging from 0·5 to 0·7 of thechord length for cones of semi-angle 10° and 20°,indicate that the effect of boundary layer is toslightly reduce the magnitude of the invisciddamping derivative. For blunt cones at angles ofattack less than 5°, this was in good agreement withthe limited experimental data available.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 99 , Issue 982 , February 1995 , pp. 69 - 74
Copyright
Copyright © Royal Aeronautical Society 1995 

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.)

Article purchase

Temporarily unavailable

References

1. Khalid, M. and East, R.A. High Mach number dynamic stability of pointed cones at small angles of attack, October 1980, AIAA J, p 18.Google Scholar
2. Khalid, M. High Mach number dynamic stability of blunt cones at angle of attack, Aeronaut J, November 1992, 96, (959), pp 356–359.Google Scholar
3. Chernyi, G.G. Introduction to Hypersonic Flow, Prebstein, R.F. (trans & ed), Academic Press New York and London, 1961.Google Scholar
4. Krasnov, N.F. Aerodynamics of Bodies of Revolution, Deane, N.M. (ed) American Elsevier Publishing, New York, 1970.Google Scholar
5. Eggers, A.J. 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
6. Eggers, A.J. On the calculation of flow about objects travelling at supersonic speeds, NACA TN-2811, 1952.Google Scholar
7. Khalid, M. A Theoretical and Experimental Study of the Hypersonic Dynamic Stability of Blunt Axisymmetric Conical and Power-Law Shaped Bodies, PhD Thesis, University of Southampton, England, 1977.Google Scholar
8. Khalid, M. and East, R.A. Stability derivatives of blunt cones at high Mach number, Aeronaut Q, November 1979, 30, pp 559–590.Google Scholar
9. Kopal, Z. Tables of supersonic flow around cone at large yaw, MIT TR No 5, 1949.Google Scholar
10. Orlik-ruckemann, K.J. Dynamic Viscous Pressure Interaction in Hypersonic Flow, NRC Aeronautical Report LR-535, July 1970.Google Scholar
11. Pinkus, O. and Cousin, S.B. Three-dimensional boundary layer on cones at small angles of attack, ASME Transactions, December 1968, pp 634–640.Google Scholar
12. Moore, F.K. Laminar boundary layer on a circular cone in supersonic flow at a small angle of attack, NACA TN-2521, October 1951.Google Scholar
13. Stetson, K.R. Boundary layer separation on slender cones at angle of attack, AIAA J, May 1972.Google Scholar
14. East, R.A. and Hutt, G.R. Hypersonic static and dynamic stability of axi symmetric shapes — a comparison of prediction methods and experiment, AGARD Symposium on Aerodynamics of Hypersonic Lifting Vehicles, April 1987.Google Scholar
15. Hayes, W.D. and Probstein, R.F. Hypersonic Flow Theory, Academic Press 1959.Google Scholar
16. Schueler, C.J. Dynamic stability results for a 10° cone at Mach numbers 0–8 to 20, AEDC-TDR 64–226, December 1964.Google Scholar
17. Brong, E. A. The unsteady flow field about a right circular cone in unsteady flight, FDL-TDR 64–148, January 1967.Google Scholar