Heat-Transfer Effects of Surface Protuberances on the X-15 Airplane
Watts, Joe D. and Olinger, Frank V. (1968) Heat-Transfer Effects of Surface Protuberances on the X-15 Airplane. Technical Report NASA TM X-1566, Research Engineering, NASA Dryden Flight Research Center.
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Abstract
The heat-transfer effects of flow separation forced by two types of surface protuberances on the fuselage of the X-15 airplane were measured in flight at Mach numbers near 5 and local Reynolds numbers of approximately 5 x 10 to the 7th power. The two protuberance configurations were a 0.20-inch (0.51-centimeter-) forward-and-aft-facing step and a sine wave of 0.20-inch- (0.51-centimeter-) amplitude at a right angle to the stream direction. Heat-transfer coefficients were calculated from measured skin temperatures across the protuberances and normalized to measured smooth-panel data. The variation of the heat-transfer coefficient across the protuberances ranged from 0.09 to 2.23 times the smooth-surface value. Flight data were compared with wind-tunnel data measured in turbulent flow.
| EPrint Type: | NASA Technical Memorandum |
|---|---|
| Keywords: | Heat transfer, Separated flow, Skin temperature (biology), Turbulent flow, X-15 aircraft |
| Subjects: | (01 - 09) Aeronautics: (01) Aeronautics - General Aircraft/Project: X-15 |
| ID Code: | 833 |
| Deposited On: | 05 April 2006 |
| Additional Information: | 29 pages. |
