THE MEASUREMENT AND COMPARISON WITH THEORY OF HEAT TRANSFER FROM SIMILAR LAMINAR BOUNDARY LAYERS TO AERODYNAMIC BODIES IN SUPERSONIC AND HYPERSONIC GAS STREAMS. Report No. 569
The experimental measurement of small rates of heat transfer to wind tunnel models from laminar compressible similar boundary layers at supersonic and hypersonic free stream Mach numbers is described. Wind tunnel models are developed having specified surface Mach number distributions. A method is developed and tested for measuring isothermal heat transfer to cold wind tunnel models. Measurements are made of the recovery temperature and heat transfer rates on cold and hot models respectively with similar boundary layers in both favorab'e and adverse pressure gradients at free stream Mach numbcrs of two and eleven respectively. A correction based on exact solutions for arbitrary Prandtl numbers is used to accommodate the similar solutions, assuming a Prandtl number of one for the test gases. In tests carried out in the Mach-two free stream, agreement is obtained between theory and experiment except in a region where the similarity requirement on the surface Mach number distribution is singular. The tests in the adverse pressure gradient suggest that the upper-branch similar solutions are encountered in practice. The recovery temperatures are found to agree with values predicted by equating the local recovery factor to the square root of the Prandtl number. (auth)
- Research Organization:
- Princeton Univ., N.J.
- NSA Number:
- NSA-16-017792
- OSTI ID:
- 4842773
- Report Number(s):
- AFOSR-1591
- Country of Publication:
- United States
- Language:
- English
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