This paper describes the extension and application of the Parabolized Stability Equations (PSE) to the stability and transition of the supersonic three-dimensional laminar boundary layer on a swept wing. The problem formulation uses a general coordinate transformation for arbitrary curvilinear body-fitted computational grids. Some testing using these coordinates is briefly described to help validate the software used for the investigation. The disturbance amplitude ratios as a function of chord position for supersonic (Mach 1.5) boundary layers on untapered, untwisted wings of different sweep angles are then presented and compared with those obtained from local parallel analyses.
Stability and transition on swept wings
AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States
1993-01-01
Conference paper
No indication
English
Stability and transition on swept wings
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