By L. S. Fletcher
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Extra info for Aerodynamic Heating and Thermal Protection Systems
For the VSL results, the boundary-layer edge location occurs near the location of maximum temperature. Note that the inviscid results are in good agreement with the VSL results at the boundary-layer edge location. With the approximate convective heating analysis , it also was found that good agreement with the VSL solutions was obtained if the boundary-layer edge conditions were taken to be the inviscid wall conditions computed with the approximate adiabatic inviscid flowfieId analysis. With the VSL analysis, the convective heating-rate values (both laminar and turbulent) are essentially the same, whether radiation is or is not included in the calculation.
The corresponding results, which show the effect of carbon-phenolic injection on the stagnation-point radiative heating, are presented in Fig. 19. The results are presented in terms of the radiative heating ratio q r /(q r )^ : _Q vs the dimensional mass injection rate. 0 B' = m/N st Fig. 18 Effect of carbon-phenolic injection on stagnation-point convective heating for the large probe (VSL results). 22 MOSS, ZOBY, SUTTON, AND ANDERSON is very sensitive to entry conditions. 72 during the earlier portion of the heat pulse.
Likewise, when plotted against the gap width D (Fig. 12), there is consistency in the results. It is probable that whether the flow is laminar or turbulent also affects the cove inlet pressure drop. The aforementioned results are similar to those obtained by Brown and Jakubowski10 and Jakubowski and Lewis11 in the region downstream of a rearward-facing step with suction. The theory of Inger12 supports the results of Refs. 10 and 11. The geometry near the inlet to the elevon cove is similar to a rearward-facing step except that there is a gentle ramp extending from the back of the step up to the surface of the elevon.