HEMISPHERE-CYLINDER HEAT TRANSFER STUDY.
Final rept. Mar 62-Sep 62,
AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OHIO DIRECTORATE OF ENGINEERING STANDARDS
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The stagnation point heat transfer rate to a series of hemisphere-cylinder with varying nose radius was measured at M approx. equal 4 with stagnation temperatures 2500 R to 4500 R. The experimental resultcompared to current theories for a velocity range of 5000 infinity 7000 ftsec and an enthalpy ratio range of 0.08 hw over hs 0.50. The experimental data indicates that agreement with individual theory is obtained for specific ranges of wall enthalpy ratio, and no one theory adequately predicts the entire range. Author