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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
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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 

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