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

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.

name of conference

• Volume 1: Fora, Parts A and B

authors

• Reed, Helen
• Saric, William

published proceedings

• Volume 1: Fora, Parts A and B

author list (cited authors)

• Saric, W. S., & Reed, H. L.

citation count

• 3

complete list of authors

• Saric, William S||Reed, Helen L

publication date

• January 2002

publisher

• ASME International  Publisher

keywords

• 40 Engineering
• 4001 Aerospace Engineering
• 4012 Fluid Mechanics And Thermal Engineering

Digital Object Identifier (DOI)

• 10.1115/fedsm2002-31258

start page

• 1475

end page

• 1480

volume

• 257

issue

• 1 B

URL

• http://dx.doi.org/10.1115/fedsm2002-31258