An Experimental Method for Determining Heat Transfer Distributions on Blunt Bodies at Hypersonic Mach Numbers

摘要

Experimental convective heat transfer distributions on a hemisphere-cylinder configuration were obtained using slug calorimeters and Gardon gages. Wind tunnel tests were conducted at a nominal Mach number of 10 over a free-stream Reynolds number range from 310,000 to 1,040,000 based on the model diameter (5.80 inches). The data were compared with theoretical heat transfer values and data obtained with thin-skin calorimetric wind tunnel models. The slug calorimeter data were highly time dependent due to conduction heat losses; consequently, the data did not compare favorably with theoretical predictions. Gardon gage indicated heat transfer was in very good agreement with both theoretical values and data from other sources. (Author)