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Thesis - Campus Access Only
Master of Science (MS)
Heating, Hypersonic, Radiative, Reentry
This thesis attempts to estimate stagnation point radiative heat flux for hypervelocity reentry vehicles. To begin, a shock shape is assumed. Using the inverse method developed by Maslen, the body that supports such a shock is calculated. High temperature equilibrium theory that accounts for chemical reactions in air was incorporated into Maslen’s Method. Using the calculated air temperature and density behind the bow-shock, radiative heat flux is then calculated at the stagnation point. When a non-grey transparent gas was assumed in the shock-layer, a radiative heat flux at the stagnation point on the vehicle with a nose radius equal to that of the Apollo Command Module was calculated to be 2.9 〖×10〗^4 BTU⁄(〖ft〗^2 s), using a free-stream velocity of 36,000 feet per second at an altitude of 170,000 feet. This was approximately 18% less than the flux calculated for an infinite slab of comparable gas conditions and shock-layer thickness. When an emitting and absorbing shock-layer were modeled with radiative cooling, agreement with rigorous analysis from previously published data were in agreement on the order of a 1.2 to 13.7% difference.
Carlozzi, Alexander Anthony, "Estimating Stagnation-Point Radiative Heating Using Maslen's Inverse Method And High-Temperature Equilibrium Air Properties" (2015). Master's Theses. 4533.