Results of Supersonic Heat-Transfer Studies on Blunt Swept Leading Edges.
Aerodynamic investigative study 1967-1968,
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
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Stagnation-line heat-transfer distributions were obtained on blunt swept leading edges at Mach 3.66 and a Reynolds number per foot of 210,000. Pressure distributions were obtained for comparable test conditions. The results illustrate the effects of various flow nonuniformities on leading-edge heat transfer and pressure, including those arising from finite span and nonuniform leading-edge sweep free-stream nonuniformity induced by the bow shock of typical blunt body boundary-layer interaction near the leading-edge root and impingement of a trailing-tip vortex. None of these effects can be predicted analytically as yet, and all may lead to significant deviation from the levels based on infinite-cylinder theory. The importance of the individual results are discussed, and, where possible, appropriate design criteria are presented. Author
- Air- and Space-Launched Guided Missiles
- Fluid Mechanics