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

  • R. M. Krek (a1) and R. J. Stalker (a1)

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.

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1. Stalker, R.J., Development of a hypervelocity wind tunnel, Aeronaut J, 1972, 76, pp 374–384.
2. Stalker, R.J., Hypervelocity aerodynamics with chemical non equilibrium, Annual Review of Fluid Mechanics, 1989, 21, pp 37–60.
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.
4. Stalker, R.J. Shock tunnels for real gas hypersonics, AGARD Conference Proceedings No. 428, Aerodynamics of Hypersonic Lifting Vehicles, 1987, pp 4–10.
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.
6. McLntosh, M.K. Computer Program for the Numerical Calculation of Frozen and Equilibrium Conditions in Shock Tunnels, Report, Dept of Physics, ANU, 1968.
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.
8. Hayes, W.D. and Probstein, R.F. Hypersonic Flow Theory, Vol. 1, Inviscid Flows, Academic Press, London, 1966.
9. Throckmorton, D.A. and Zoby, E.V. Orbiter entry leeside heat-transfer data analysis, J Spacecr Rockets, 1983, 20, (6), pp 524–530.
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.
11. Stalker, R.J. Nonequilibrium flow over delta wings with detached shock waves, AIM J, 1982, 20, pp 1633–1639.
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.
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.
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.
15. Holden, M. S. Establishment time of laminar separated flows, AIAA J, 9, (11), pp 2296–2298.
16. Schultz, D.L. and Jones, T.V. Heat transfer measurements in short duration hypersonic facilities, AGARDograph No. 165, February 1973.
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.
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.
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.
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.
21. Yaping, He. Transition and Heat Transfer in the Compressible Boundary Layer over a Flat Plate, Submitted for PhD University of Queensland 1991.
22. Henderson, A. Jr Hypersonic viscous flows, Chapter 3 of Modern Development in Gas Dynamics, Plenum Press, 1969.
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.
24. Sutton, J. and Graves, R.A. A General Stagnation Point Convective Heating Equation for Arbitary Gas Mixtures. NASA TR R-376, 1972.

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

  • R. M. Krek (a1) and R. J. Stalker (a1)

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