Entry Heating and Thermal Protection Paas69 by W. B. Olstad

By W. B. Olstad

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3 sec. the time of peak stagnation-point heating. The reason turbulence has such an adverse effect on the radiative heating with ablation injection is that turbulence significantly alters the structure and composition of the shock layer. Figures 8 and 9 demonstrate the effect of turbulence on composition, velocity, and temperature profiles at the end of the hyperboloid. These results demonstrate the dramatic effect of turbulence on the ablation-layer thickness (Fig. 8a) and the chemical composition within the ablation layer (Fig.

At 12 times along the entry trajectory, forebody solutions for no injection were obtained, while coupled forebody solutions were obtained at seven of these times. A summary of the surfaceintegrated heating rates and the integrated ablation massloss rates are presented in Table 3. The convective power input with coupled ablation injection is much less than the corresponding no-injection case. However, these results show that the radiative power input is comparable, and for some cases, even greater than the corresponding results for no injection.

22 s apparatus. Without density "i Present With density j calculations Kendall et al. 9 model Beckwith and Bushnell ^Bonnet model ) and ^3 Cebeci and Smith model 25 100 ) Evans Hopkins and Nerem data Tri p 80 60 40 20 0 2 4 6 8 10 12 14 16 18 Distance from Leading Edge (cm) Fig. 22 Purchased from American Institute of Aeronautics and Astronautics PREDICTING OFF-STAGNATION-POINT FLOWFIELDS C\J o A Present method O Experiment - glass wall 37 G Experiment - steel wall § CD Mirels 27 1 2 3 4 5 6 Shock Mach Number, M 7 8 Fig.

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