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Volume:7, Issue: 12, 2013 Page No: 2389 - 2391

International Journal of Mechanical, Industrial and Aerospace Sciences

ISSN: 2517-9950

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DOI:10.5281/zenodo.1089106 BibTeX JSON

An Accurate Prediction of Surface Temperature History in a Supersonic Flight

In the present study, the surface temperature history of the adaptor part in a two-stage supersonic launch vehicle is accurately predicted. The full Navier-Stokes equations are used to estimate the aerodynamic heat flux and the one-dimensional heat conduction in solid phase is used to compute the temperature history. The instantaneous surface temperature is used to improve the applied heat flux, to improve the accuracy of the results.

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