Abstract
As a result of an extensive experimental study, a technique has been developed for predicting shock shapes, pressures, and turbulent heat-transfer rates on the leading edge of a fin, swept wing, antenna, or similar highly swept protuberance near its intersection with a high-velocity vehicle. Comparison of predictions with data of the present experiment and those of others indicates good agreement. While pressures in the intersection region are higher than infinite swept cylinder theory predictions, heat-transfer rates can be either significantly greater or less than values predicted by this theory depending on local flow conditions and geometry.
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