STAGNATION-POINT HEAT TRANSFER MEASUREMENTS IN HYPERSONIC, LOW-DENSITY FLOW. Paper 7 of GENERAL RESEARCH IN FLIGHT SCIENCES, JANUARY 1959-JANUARY 1960. VOLUME I. FLUID MECHANICS. PART 2
Technical Report
·
OSTI ID:4166674
An experimental investigation of the heat-transfer rates at the stagnation point of a hemisphere cylinder in a hypersonic, low-density stream is described. The experiments were undertaken to assess prior theoretical predictions that such heat-transfer rates would be greater than those predicted by the more customary boundary-layer theories Experiments were conducted in a shock-tunnel adaptation of a combustion-driven shock tube at free-stream Reynolds numbers, based on the one-inch nose radius, from 170 to 2700 and a Mach number of about 6. The test results appear to be in agreement with the theoretical predictions. (auth)
- Research Organization:
- Lockheed Aircraft Corp. Missiles and Space Div., Sunnyvale, Calif.
- NSA Number:
- NSA-14-019096
- OSTI ID:
- 4166674
- Report Number(s):
- LMSD-288139(Vol. I, Pt. 2)(Pap
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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