Abstract
Comparative heat flux measurements for a sharp cone model were conducted by utilizing a high Reynolds number shock tunnel JF8A, a high-enthalpy shock tunnel JF10, and a large-scale shock tunnel JF12 at the Key Laboratory of High Temperature Gas Dynamics (LHD), Institute of Mechanics, Chinese Academy of Sciences, which were responsible for providing the nonequilibrium or perfect gas flows. Through the assessment of data accuracy and consistency between each facility, we aim to compare the heat transfer data of a sharp cone taken in them under a totally different kind of freestream conditions. A parameter, defined as the product of the Stanton number and the square root of the Reynolds number, was found to be more characteristic for the aerodynamic heating phenomena encountered in hypersonic flight under laminar flows. This parameter can almost eliminate the variability caused by the different flow conditions, and it should be a more preferable parameter for the reduction of the ground experimental data and the extrapolation to flight.
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Acknowledgments
This work was supported by the National Natural Science Foundation of China (Grant Nos. 11402275 and 11472280).
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Wang, Q. et al. (2019). Comparative Heat Flux Measurement of a Sharp Cone Between Three Hypersonic Test Facilities at LHD. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 2. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91017-8_122
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DOI: https://doi.org/10.1007/978-3-319-91017-8_122
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