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Development of a hypervelocity wind tunnel

Published online by Cambridge University Press:  04 July 2016

R. J. Stalker*
Affiliation:
Department of Physics, The Australian National University, Canberra

Extract

Wind tunnels are far older than powered flight. Including the aeroplane of the Wright Brothers, the introduction of new types of aircraft has almost invariably been preceded by extensive model investigation in wind tunnels. These investigations can be classified into two broad areas. One is development testing, in which models are tested and modified with the purpose of producing a specific aircraft configuration. The other covers the research and general experimentation which is necessary for the determination of the new rules governing entry into a new régime of flight. Thus, wind tunnels may conveniently be referred to either as “development” or as “research” wind tunnels, according to the type of work which is done in them.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 1972 

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References

1. Ferri, A. Review of problems in application of supersonic combustion. Journal of the Royal Aeronautical Society, Vol 68, p. 574, 1964.Google Scholar
2. Lukasiewicz, J., Whitfield, J. D. and Jackson, R. Aerodynamic testing at Mach numbers from 15 to 20. ARS Progress in Astronautics and Rocketry: Hypersonic Flow Research, edited by Riddell, F. R., Academic Press Inc., New York, Vol 7, p. 473, 1962.Google Scholar
3. Bray, K. N. C. Evaluation of the hypersonic gun tunnel. ARS Progress in Astronautics and Rocketry: Hypersonic Flow Research, edited by Riddell, F. R., Academic Press Inc., New York, Vol 7, p. 547, 1962.Google Scholar
4. Wittliff, C. E., Wilson, M. R. and Hertzberg, A. The tailored-interface hypersonic shock tunnel, J. Aerospace Sci., Vol 26, p. 219, 1959.Google Scholar
5. Stalker, R. J. Isentropic compression of shock tube driver gas, ARS Journal, Vol 30, p. 564, 1960 Google Scholar
6. Stalker, R. J. A study of the free-piston shock tunnel, AIAA Journal, Vol 5, p. 2160, 1967.Google Scholar
7. Rose, P. H. Development of the calorimeter heat transfer gauge for use in shock tubes, Rev. Sci. Instr., Vol 29, p. 557, 1958.Google Scholar
8. Hertzberg, A., Wittliff, E. C. and Hall, J. G. Develop ment of the shock tunnel and its application to hyper sonic flight, ARS Progress in Astronautics and Rocketry: Hypersonic Flow Research, edited by Riddell, F. R., Academic Press Inc., New York, Vol 7, p. 701, 1962.Google Scholar
9. Griffith, B. J. and Boylan, D. E. Reynolds and Mach number simulation of Apollo and Gemini re-entry and comparison with flight, Agard Conference Proceedings No. 30, (pre-print), Hypersonic boundary layers and flow fields, May 1968.Google Scholar
10. Teare, J. D. High temperature phenomena, Research Frontiers in Fluid Dynamics, edited by Seeger, R. J. and Temple, G., Interscience, New York, p. 406, 1965.Google Scholar
11. Leonard, R. L. and Rose, P. H. Feasibility of a high- performance aerodynamic impulse facility, AIAA Journal, Vol 6, p. 448, 1968.Google Scholar