Accession Number:

AD0262485

Title:

EFFECT OF ROUGHNESS ON TRANSITION IN SUPERSONIC FLOW

Descriptive Note:

Corporate Author:

ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)

Personal Author(s):

Report Date:

1960-04-01

Pagination or Media Count:

19.0

Abstract:

Experiments were carried out in the 12-in. supersonic wind tunnel to investigate the effect of three-dimensional roughness elements spheres on boundary-layer transition on a 10 degree apex angle cone without heat transfer. The local Mach number for these tests was 2.71. The data show clearly that the minimum effective size of trip required to bring transition to its lowest Reynolds number varies as the one-fourth power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by the simple expression Reynolds number based on displacement thickness 10501 12gamma - 1 Mach number based on displacement thickness squared roughness element heightboundary layer displacement thickness-2. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE