Requirement to design light weight heat shields for sounding rockets has focused attention on solution of general equations of fluid dynamics coupled with mathematical ablation model for subliming ablators; to test accuracy, of theory and model, two monitored inflight rocket experiments were performed using Black Brant rockets as experimental platforms; comparison of experimental data and results obtained from theory, programmed for IBM 360 computer shows good agreement over wide range of flight conditions for continuum supersonic and hypersonic regimes. (29773)
Ablative stagnation point heat transfer
CASI Trans
1969
6 pages
Article (Journal)
English
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