By L. S. Fletcher
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Extra info for Aerodynamic Heating and Thermal Protection Systems
Cooper, L. and Putz, K. , "Generalized Flow in Gaps and Slots Including the Effects of Ablation," Journal of Spacecraft and Rockets, Vol. 11, May 1974, pp. 287-294. 5 Kirlin, R. L. and Schmitt, D. , MCR-73-117, June 1973. 6 Duffy, R. , "Post-test Study of the Cove Heating Distribution for the Eleven Cove Seal Test at NASA JSC," Rockwell International, internal letter SEH-ITA-77-106 to G. Mauss, May 6, 1977. 7 Shapiro, A. , The Dynamics and Thermodynamics of Compressible Fluid Flow, Vol. 1, Ronald Press, New York, 1953.
2) The simulation of the trajectory closely approached that of the flight design trajectory in terms of the correlation parameter, the internal heat load in the experiments being about 93% of flight. The simulation was especially good for narrow seal gaps where there was a small pressure drop at the cove. 6 mm. 4) There was a significant pressure drop at the cove for the large seal gap widths in the experiments. This pressure drop seems to be related to the mass flow through the cove and to external boundary-layer properties.
Comparisons show that the approximate analysis provides acceptable agreement with the more detailed VSL results. However, the agreement between inviscid and VSL radiative heating results is acceptable only when the effect of the strongly absorbing boundary layer (which is included in the VSL analysis) is accounted for. Stagnation-point results for the large probe show that as much as 30$ of the radiative flux incident on the wall is absorbed in the unblown boundary layer. The nature of the radiative heating environment is such that the stagnation region heating is due to both continuum (molecular band transitions are included) and line transitions.