Hostname: page-component-cb9f654ff-hqlzj Total loading time: 0 Render date: 2025-08-21T10:06:27.865Z Has data issue: false hasContentIssue false
  • English
  • Français

Heat transfer measurements on a biconic inhypervelocity nitrogen flow

Published online by Cambridge University Press:  04 July 2016

S. L. Gai ,
T. Cain  and
W. S. Joe
S. L. Gai
Affiliation:
Department of Mechanical Engineering, University College, University of New South Wales, Australian Defence Force Academy, Canberra
T. Cain
Affiliation:
Department of Physics & Theoretical Physics, The Australian National University, Canberra
W. S. Joe
Affiliation:
Department of Physics & Theoretical Physics, The Australian National University, Canberra
Get access Rights & Permissions [Opens in a new window]

Abstract

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.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 946 , July 1991 , pp. 187 - 193
Copyright
Copyright © Royal Aeronautical Society 1991 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

1. Walberg, G. D. A survey of aero-assisted orbit transfer, J Spacecraft Rockets, 1985, 22, p 3.Google Scholar
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.Google Scholar
3. Miller, C. G. Experimental and Predicted Heating Distributions for Biconics at Incidence in Air at Mach 10, NASA Tech. Paper 2334, Nov. 1984.Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
7. Stalker, R. J. Free Piston Shock Tunnel T3, A Facility Handbook, Univ. of Queensland, 1985.Google Scholar
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.Google Scholar
9. Schultz, D. L. and Jones, T. V. Heat Transfer Measurements in Short Duration Facilities, AGARD RN 165, Feb. 1973.Google Scholar
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.Google Scholar
11. Waldron, H. F. Viscous hypersonic flow over printed cones at low Reynolds numbers, AIAA J, 1967, 5, p 208.Google Scholar
12. Sutton, J. and Graves, R. A. A General Stagnation Point Convective Heating Equation for Arbitrary Gas Mixtures, NASA TR-R-376, Nov. 1972.Google Scholar
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.Google Scholar
14. Stetson, K. F. Boundary layer separation on slender cones at angles of attack, AIAA J, 1972, 10, p 642.Google Scholar
15. Hornung, H. G. Non-equilibrium dissociating nitrogen flow over spheres and circular cylinders, J Fluid Mech, 1972, 53, p 149.Google Scholar
16. Kewley, D. J. and Hornung, H. G. Free piston shock tube study of nitrogen dissociation. Chem Phys Let, 1974, 25, p 531.Google Scholar
17. Macrossan, M. N. Hypervelocity flow of dissociating nitrogen downstream of a blunt nose, To appear in J Fluid Mech, 1991.Google Scholar
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.Google Scholar
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.Google Scholar