Computational study of transition front on a swept wing leading-edge modelThe e(N) method is employed with Navier-Stokes calculations to study 3D supersonic boundary layers at the leading-edge region of swept wings with attention given to the conditions for linear stability. Mean-flow profiles are computed as solutions to the Navier-Stokes equations, and the e(N) method is used to identify the onset of the transition. Specific treatment is given to the identification of parameters which affect the transition such as free-stream Reynolds number, wall cooling, and boundary-layer suction levels. The boundary layer can be stabilized to below N=10 levels in all locations by utilizing distributed suction, and enhanced stabilization can also be achieved by employing wall cooling and reduced free-stream Reynolds numbers. This study presents key calculations for corresponding experimental investigations by shedding light on requirements for test conditions and measurement requirements.
Document ID
19920062878
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Iyer, Venkit (Vigyan, Inc. Hampton, VA, United States)
Spall, Robert E. (South Alabama, University Mobile, AL, United States)
Dagenhart, J. R. (NASA Langley Research Center Hampton, VA, United States)