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Shock-boundary-layer interaction in flightA 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.
Document ID
19890011557
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bertelrud, Arild (High Technology Corp. Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Publication Information
Publication: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1
Subject Category
Aerodynamics
Accession Number
89N20928
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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