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首页> 美国政府科技报告 >Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows
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Evaluation of a technique to generate artificially thickened boundary layers in supersonic and hypersonic flows

机译：评估在超音速和高超音速流动中产生人工增厚边界层的技术

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摘要

The feasibility of using a contoured honeycomb model to generate a thick boundary layer in high-speed, compressible flow was investigated. The contour of the honeycomb was tailored to selectively remove momentum in a minimum of streamwise distance to create an artificially thickened turbulent boundary layer. Three wind tunnel experiments were conducted to verify the concept. Results indicate that this technique is a viable concept, especially for high-speed inlet testing applications. In addition, the compactness of the honeycomb boundary layer simulator allows relatively easy integration into existing wind tunnel model hardware.

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