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Heat transfer measurements on a biconic in hypervelocity nitrogen flow

  • S. L. Gai (a1), T. Cain (a2) and W. S. Joe (a2)


Heat transfer rates on a straight biconic, an attractive configuration for an aero-assisted orbital transfer vehicle, were made in the ANU T3 shock tunnel at various angles of attack and a stagnation enthalpy of 26 MJ/kg, equivalent to a flight speed of 7-2 km/s. The heat transfer database at this higher enthalpy has been compared with the data obtained on the same model in hypersonic and hypervelocity facilities elsewhere. The non-equilibrium flow effects on the model have been discussed in terms of the Hornung reaction rate parameter Ω.



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1. Walberg, G. D. A survey of aero-assisted orbit transfer, J Spacecraft Rockets, 1985, 22, p 3.
2. Miller, G. G. and Gnoffo, P. A. Pressure Distributions and Shock Shapes for 12-84°/7° On-axis and Bent Biconics in Air at Mach 6, NASA TM-83-222, Dec. 1981.
3. Miller, C. G. Experimental and Predicted Heating Distributions for Biconics at Incidence in Air at Mach 10, NASA Tech. Paper 2334, Nov. 1984.
4. Miller, C. G.,Blackstock, T. A., Helms, V. T. and Midden, R. E. An Experimental Investigation of Control Surface Effectiveness and Real Gas Simulation for Biconics, AIAA-83- 0213, Jan, 1983.
5. Miller, C. G., Micol, J. R. and Gnoffo, P. A. Laminar Heat Transfer Distributions on Biconics at Incidence in Hypersonic Hypervelocity Flows, NASA Tech. Paper 2213, Jan. 1985.
6. Miller, C. G. and Jones, J. J. Development and Performance of the NASA Langley Research Center Expansion Tube/ Tunnel, a hypersonic hypervelocity real gas facility, Proceedings of the 14th Int. Symp. on Shock Tubes and Waves, Sydney, Australia, Aug. 1983, p 363.
7. Stalker, R. J. Free Piston Shock Tunnel T3, A Facility Handbook, Univ. of Queensland, 1985.
8. Gai, S. L., Cain, T. M., Joe, W. S., Sandeman, R. J. and Miller, C. G. Heat transfer measurements on biconics at incidence in hypersonic high enthalpy air and nitrogen flows, Proceedings of the 16th ICAS Congress, Jerusalem, Israel, Sept. 1988.
9. Schultz, D. L. and Jones, T. V. Heat Transfer Measurements in Short Duration Facilities, AGARD RN 165, Feb. 1973.
10. Cheng, H. K. Hypersonic Flow With Combined Leading Edge Bluntness and Boundary Layer Displacement Effect, Rept. No. AF-1285, Cornell Aero. Lab., Aug. 1960.
11. Waldron, H. F. Viscous hypersonic flow over printed cones at low Reynolds numbers, AIAA J, 1967, 5, p 208.
12. Sutton, J. and Graves, R. A. A General Stagnation Point Convective Heating Equation for Arbitrary Gas Mixtures, NASA TR-R-376, Nov. 1972.
13. Miller, C. G. in: Aerodynamic Control Research — Generic Planetary and Technology Development, Final Report, Ed. Cruz, M.I., NASA JPL Rept. D-691, May 1983.
14. Stetson, K. F. Boundary layer separation on slender cones at angles of attack, AIAA J, 1972, 10, p 642.
15. Hornung, H. G. Non-equilibrium dissociating nitrogen flow over spheres and circular cylinders, J Fluid Mech, 1972, 53, p 149.
16. Kewley, D. J. and Hornung, H. G. Free piston shock tube study of nitrogen dissociation. Chem Phys Let, 1974, 25, p 531.
17. Macrossan, M. N. Hypervelocity flow of dissociating nitrogen downstream of a blunt nose, To appear in J Fluid Mech, 1991.
18. East, R. A., Stalker, R. J. and Baird, J. P. Measurements and heat transfer to a flat plate in a dissociated high enthalpy laminar air flow, J Fluid Mech, 1980, 97, p 673.
19. Gai, S. L., Reynolds, N. T., Ross, C. and Baird, J. P. Measurements of heat transfer in separated high enthalpy dissociated laminar hypersonic flow behind a step. J Fluid Mech, 1989, 199, p 541.

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Heat transfer measurements on a biconic in hypervelocity nitrogen flow

  • S. L. Gai (a1), T. Cain (a2) and W. S. Joe (a2)


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