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- W2909166599 abstract "This paper describes the use of distributed-roughness-element (DRE) patterns along a Mach 2 design swept-wing leading edge to increase the laminar flow extent and thereby reduce drag. One swept-wing model was tested in a supersonic wind tunnel as well as beneath a supersonic flight vehicle. Wing model surface data acquired during these tests included pressures, temperatures, and boundary-layer transition locations. Similarities and differences in experimental results are discussed. While wind tunnel and flight results show some differences, the wind tunnel results still provide key insights necessary for understanding how to design effective DRE patterns for use in flight applications. Experimental results demonstrate a DRE flow control effect observed in flight similar to that observed in the wind tunnel. Finally, a different perspective is discussed concerning what flow control role RE patterns might perform in any future swept-wing laminar flow control applications." @default.
- W2909166599 created "2019-01-25" @default.
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- W2909166599 date "2019-01-06" @default.
- W2909166599 modified "2023-10-06" @default.
- W2909166599 title "Supersonic Crossflow Transition Control in Ground and Flight Tests" @default.
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- W2909166599 doi "https://doi.org/10.2514/6.2019-1651" @default.
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