This research paper discusses constructing a unified framework to develop
a full-rate scheme for hypersonic heating calculations. The method uses a flow tracing
technique with normal phase vector adjustment in a non-structured delineated grid
combined with empirical formulations for convective heat transfer standing and non-standing
heat flow engineering. This is done using dev-C++ programming in the C++ language
environment. Comparisons of the aerodynamic thermal environment with wind tunnel
experimental data for the Space Shuttle and Apollo return capsules and standing
point heat transfer measurements for the Fire II return capsule was carried out
in the hypersonic Mach number range of 6 - 35 Ma. The tests were carried out on an 11th Gen Intel(R)
Core(TM) i5-1135G7 processor with a valuable test time of 45mins. The agreement is good,
but due to the complexity of the space shuttle tail, the measurements are still
subject to large errors compared to wind tunnel experiments. A comparison of the
measured Fire-II return capsule standing-point heat values with the theory for calculating
standing-point heat fluxes simulated using Fay & Riddell and wind tunnel experiments
is provided to verify the validity of this procedure for hypersonic vehicle heat
transfer prediction. The heat fluxes assessed using this method for different aerodynamic
profiles of hypersonic vehicles agree very well with the theoretical solution.
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