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Heat transfer rate and surface pressure measurements in short duration hypersonic flow

Published online by Cambridge University Press:  18 October 2019

M. Saiprakash Open the ORCID record for M. Saiprakash [Opens in a new window] ,
C. Senthil Kumar ,
G. Kadam Sunil ,
S.P. Rampratap ,
V. Shanmugam  and
G. Balu
M. Saiprakash*
Affiliation:
Department of Aerospace Engineering, MIT Campus, Anna University, Chennai, India
C. Senthil Kumar
Affiliation:
Department of Aerospace Engineering, MIT Campus, Anna University, Chennai, India
G. Kadam Sunil
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
S.P. Rampratap
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
V. Shanmugam
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
G. Balu
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
*
saiaero87@gmail.com
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Abstract

Experiments were carried out with air as the test gas to obtain the surface convective heating rate and surface pressure distribution on blunt and sharp cone models flying at hypersonic speeds. Tests were performed in a hypersonic shock tunnel at two different angles of attack: ${0}^\circ$ and ${5}^\circ$ with angles of rotation $\phi = {0}^\circ, {90}^\circ$, and ${180}^\circ$. The experiments were conducted at a stagnation enthalpy of 1.4MJ/kg, flow Mach number of 6.56 and free stream Reynolds number based on the model length of $9.1 \times {10}^{5}$. The effective test time of the shock tunnel is 3ms. The results obtained for cone model with a bluntness ratio of 0.2 were compared with sharp cone models for $\alpha ={0}^\circ$. The measured stagnation heat transfer value matched well with the theoretical value predicted by the Fay and Riddell correlation and with the CFD results.

Keywords

hypersonic flow over the cone modelheat transfer in hypersonic flowheat transfer in hypersonic flowshock waves in hypersonic flow
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1269 , November 2019 , pp. 1857 - 1880
Copyright
© Royal Aeronautical Society 2019 

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Footnotes

*

Research Scholar, Department of Aerospace Engineering, Madras institute of Technology, Anna University, Chennai, India

†

Professor, Department of Aerospace Engineering, Madras institute of Technology, Anna University, Chennai, India.

‡

Scientist, Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India.

References

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