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Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

Published online by Cambridge University Press:  04 July 2016

R. M. Krek  and
R. J. Stalker
R. M. Krek
Affiliation:
University of Queensland, Brisbane, Australia
R. J. Stalker
Affiliation:
University of Queensland, Brisbane, Australia
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Abstract

Heat transfer and pressure measurements were made on a model of the United States Space Shuttle Orbiter in the University of Queensland's T4 shock tunnel at three angles of attack, with stagnation enthalpies which varied by a factor of 11, from 2·1 MJ/kg to 23 MJ/kg and normal shock Reynolds numbers which varied by a factor of 38, from 2·1 x l04 to 8·l x 105. Leeward pressure results were obtained for comparison with flight data and equilibrium calculations, but the majority of the experiments were conducted to investigate the heat transfer distributions around the shuttle model. Both the windward and leeward heat transfer results exhibit the onset of transition to turbulent flow. The leeward results are compared with flight data as well as with conventional wind tunnel data, and are used to establish trends associated with variation in the major flow and geometry parameters. It was found that although high enthalpy effects could be important, Reynolds number effects played a dominant role in determining the flow.

Type
Research Article
Information
The Aeronautical Journal , Volume 96 , Issue 957 , September 1992 , pp. 249 - 259
Copyright
Copyright © Royal Aeronautical Society 1992 

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References

1. Stalker, R.J., Development of a hypervelocity wind tunnel, Aeronaut J, 1972, 76, pp 374–384.Google Scholar
2. Stalker, R.J., Hypervelocity aerodynamics with chemical non equilibrium, Annual Review of Fluid Mechanics, 1989, 21, pp 37–60.Google Scholar
3. Hornung, H.G. and Stalker, R.J. Studies of relaxation gas dynamics in the free piston shock tunnel, In: Applied Mechanics, edited by Oertel, H. Jr, Universitat Karlsruke, 1978 pp 19–28.Google Scholar
4. Stalker, R.J. Shock tunnels for real gas hypersonics, AGARD Conference Proceedings No. 428, Aerodynamics of Hypersonic Lifting Vehicles, 1987, pp 4–10.Google Scholar
5. Stalker, R.J. and Morgan, R.G. The University of Queensland free piston shock tunnel T4 - inital operation and preliminary calibration, 4th National Space Engineering Symposium, Adelaide, 1988.Google Scholar
6. McLntosh, M.K. Computer Program for the Numerical Calculation of Frozen and Equilibrium Conditions in Shock Tunnels, Report, Dept of Physics, ANU, 1968.Google Scholar
7. Lordi, J.A., Mates, R.E. and Moselle, J.R. Computer Program for the Numerical Solution of Nonequilibrium Expansions of Reacting Gas Mixtures, NASA CR-472, 1966.Google Scholar
8. Hayes, W.D. and Probstein, R.F. Hypersonic Flow Theory, Vol. 1, Inviscid Flows, Academic Press, London, 1966.Google Scholar
9. Throckmorton, D.A. and Zoby, E.V. Orbiter entry leeside heat-transfer data analysis, J Spacecr Rockets, 1983, 20, (6), pp 524–530.Google Scholar
10. Bertin, J.J. and Goodrich, W.D. Effects of surface temperature and Reynolds number on leeward shuttle heating, J Spacecr Rockets, 1976, 13,(8), pp 473–480.Google Scholar
11. Stalker, R.J. Nonequilibrium flow over delta wings with detached shock waves, AIM J, 1982, 20, pp 1633–1639.Google Scholar
12. Helms, V.T. III An empirical method for computing leeside center-line heating on the Space Shuttle Orbiter, J Spacecr Rockets, 1983, 20, (3), pp 225.Google Scholar
13. Stalker, R.J. and Crane, K.C.A. Driver gas contamination in a high enthalpy reflected shock tunnel, AIAA J, 1978, 16, pp 277–278.Google Scholar
14. Knight, D.D. Calculation of 3-dimensional shock/turbulent boundary layer interaction generated by a sharp fin, AIAA J, 1985, 23, pp 1885–1891.Google Scholar
15. Holden, M. S. Establishment time of laminar separated flows, AIAA J, 9, (11), pp 2296–2298.Google Scholar
16. Schultz, D.L. and Jones, T.V. Heat transfer measurements in short duration hypersonic facilities, AGARDograph No. 165, February 1973.Google Scholar
17. Gai, S.L., Sanderman, R.J., Lyons, P. and Kilpin, D. Shock shape over a sphere cone in hypersonic high enthalpy flow, AIAA J, 1984, 22, (7), pp 1007–1010.Google Scholar
18. Prabhu, D.K. and Tannehill, J.C. Numerical solutions of Space Shuttle Orbiter flowfield including real gas effects, J Spacecr Rockets, 1986, 23, (3), pp 264–272.Google Scholar
19. East, R.A., Stalker, R.J and Baird, J.P. Laminar Flat Plate Heat Transfer Measurements from a Dissociated High Enthalpy Hypersonics Air Flow, AASU Report no. 338, 1977.Google Scholar
20. Poll, D.I.A. New hypothesis for transition on windward face of the Space Shuttle, J Spacecr Rockets, 1986, 23, (6), pp 605–611.Google Scholar
21. Yaping, He. Transition and Heat Transfer in the Compressible Boundary Layer over a Flat Plate, Submitted for PhD University of Queensland 1991.Google Scholar
22. Henderson, A. Jr Hypersonic viscous flows, Chapter 3 of Modern Development in Gas Dynamics, Plenum Press, 1969.Google Scholar
23. Miller, C.G. Experimental Investigation of Gamma Effects on Heat Transfer to a 0·006 Scale Shuttle Orbiter at Mach 6, AIM Paper 82-0826, 1982.Google Scholar
24. Sutton, J. and Graves, R.A. A General Stagnation Point Convective Heating Equation for Arbitary Gas Mixtures. NASA TR R-376, 1972.Google Scholar