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Control of Transition in Supersonic Boundary Layers: Experiments and Computations (Keynote)

[+] Author Affiliations
William S. Saric, Helen L. Reed

Arizona State University, Tempe, AZ

Paper No. FEDSM2002-31258, pp. 1475-1480; 6 pages
doi:10.1115/FEDSM2002-31258
From:
  • ASME 2002 Joint U.S.-European Fluids Engineering Division Conference
  • Volume 1: Fora, Parts A and B
  • Montreal, Quebec, Canada, July 14–18, 2002
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 0-7918-3615-0 | eISBN: 0-7918-3600-2
  • Copyright © 2002 by ASME

abstract

The present work addresses a technique that can lead to drag reduction on supersonic wings by means of passive laminar flow control. Recent developments in the stability and transition in swept-wing flows in low-disturbance environments have offered the promise of controlling transition without suction. It has been demonstrated in low-speed experiments that distributed roughness near the attachment line can control the crossflow instability provided the roughness spacing is below a critical value. This is extended to supersonic flow over highly swept wings where the combined computational and experimental work gives design criteria for airfoils swept beyond the characteristic Mach angle.

Copyright © 2002 by ASME

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