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- W853243150 abstract "A brief survey is given on the study of transonic shock/boundary layer effects in flight. Then the possibility of alleviating the adverse shock effects through passive shock control is discussed. A Swedish flight experiment on a swept wing attack aircraft is used to demonstrate how it is possible to reduce the extent of separated flow and increase the drag-rise Mach number significantly using a moderate amount of perforation of the surface." @default.
- W853243150 created "2016-06-24" @default.
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- W853243150 date "1989-03-01" @default.
- W853243150 modified "2023-09-23" @default.
- W853243150 title "Shock-boundary-layer interaction in flight" @default.
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