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Effects of a Source-Type Hypersonic Free Stream on the Flow Field about an Axisymmetric Cone

Published online by Cambridge University Press:  07 June 2016

Stuart B. Savage
Stuart B. Savage*
Affiliation:
Department of Civil Engineering and Applied Mechanics, McGill University
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Summary

Most hypervelocity tunnels presently make use of conical or wedge type nozzles which produce source-type flow non-uniformities in the test section. The present paper considers the effects of such free-stream non-uniformities on the flow fields about slender axisymmetric cones. The inviscid flow is considered within the framework of the Newtonian expansion procedure of Cole and simple expressions are obtained for the flow field properties in the shock layer. This inviscid analysis predicts that a free-stream gradient of a magnitude typical of present hypervelocity test facilities can cause sizeable reductions in surface pressure and increased shock-layer thickness at the aft end of long slender conical models. The cone pressure, accounting for the viscous-inviscid interaction, is obtained by applying the inviscid analysis in tangent-cone fashion to the effective body (i.e. physical cone plus boundary-layer displacement thickness). Cheng’s simple equation is used to approximate the hypersonic boundary-layer development. Large increases in the boundary-layer thickness at the aft end of the model are predicted as a consequence of the source flow effects. The analyses agree well with experimental measurements of surface pressure and boundary-layer thickness made on a 5° half-angle cone tested in the Republic 24 inch Longshot I hypervelocity shock tunnel.

Type
Research Article
Information
Aeronautical Quarterly , Volume 17 , Issue 2 , May 1966 , pp. 161 - 176
Copyright
Copyright © Royal Aeronautical Society. 1966

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References

1. Baradell, D. L. and Bertram, M. H. The blunt flat plate in hypersonic flow. NASA TN D-408, 1960.Google Scholar
2. Henderson, A. and Baradell, D. L. Recent work at Langley Research Center in the development of hypersonic helium tunnels. Proceedings of the Hypervelocity Techniques Symposium, Denver, Colorado, 1960.Google Scholar
3. Whitfield, J. D. and Norfleet, G. D. Source flow effects in conical hypervelocity nozzles. Arnold Engineering Development Center, AEDC TDR-62-116, 1962.Google Scholar
4. Burke, A. F. and Bird, K. D. The use of conical and contoured expansion nozzles in hypervelocity facilities. Cornell Aeronautical Laboratory, CAL Report 112, 1962.Google Scholar
5. Meyer, R. F. The blast wave analogy for a hypersonic source flow. National Research Council of Canada, NRC Aero. Report LR-368, 1963.Google Scholar
6. Hall, J. G. Effects of ambient nonuniformities in flow over hypersonic test bodies. Cornell Aeronautical Laboratory, CAL Report 128, 1963.Google Scholar
7. Cheng, H. K. Hypersonic flow with combined leading edge bluntness and boundary layer displacement effect. Cornell Aeronautical Laboratory, CAL Report AF-1285-A-4, 1960.Google Scholar
8. Cole, J. D. Newtonian flow theory for slender bodies. Journal of the Aeronautical Sciences, Vol. 24, p. 448, 1957.Google Scholar
9. Van Dyke, M. D. A study of hypersonic small disturbance theory. NACA Report 1194, 1954.Google Scholar
10. Cheng, H. K., Hall, J. G., Golian, T. C. and Hertzberg, A. Boundary-layer displacement and leading-edge bluntness effects in high-temperature hypersonic flow. Journal of the Aerospace Sciences, Vol. 28, p. 353, May 1961.Google Scholar
11. Cheng, H. K., Hall, J. G., Golian, T. C. and Hertzberg, , Longshot I, hypersonic free-piston tunnel. Republic Aviation Corporation, RAC Report 1884, 1963.Google Scholar
12. Cohen, C. B. and Reshotko, E. The compressible laminar boundary layer with heat transfer and arbitrary pressure gradient. NACA Report 1244, 1956.Google Scholar
13. Griffith, B. J., Deskins, H. E. and Little, H. R. Condensation studies in hotshot tunnels. AIAA Journal, Vol. 2, p. 1645, September 1964.Google Scholar