Influence of Hypersonic Inlet Cowl Lip on Flowfield Structure and Thermal Load

摘要

An asymmetrical hypersomc inlet cowl lip was numerically studied to explore a new approach of thermal protection. Comparative analyses of the flowfield structure and wall heat transfer with a symmetrical cowl lip were conducted. Results indicate that the peak heat transfer rate to the wall of the asymmetrical cowl lip decreases greatly when an impinging shock intersects a bow shock. Without the impinging shock, the location of the peak heat transfer rate occurs on the wall with a small radius, which does not coincide with the location of the air stagnation point; and the wall peak heat transfer rate of the asymmetrical cowl lip is higher than those of the symmetrical cowl lip, unless the flow attack angle to the wall with a large radius exceeds 12 deg.