Accession Number : ADA382291

Title :   An Experimental Investigation of the Effect of Surface Heating on Boundary-Layer Transition on a Flat Plate in Supersonic Flow

Descriptive Note : Technical note,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCHCENTER

Personal Author(s) : Higgins, Robert W. ; Pappas, Constantine C.

Handle / proxy Url :             Check NTIS Availability...

Report Date : APR 1951

Pagination or Media Count : 33

Abstract : Wind-tunnel tests have been performed to investigate the effect of surface heating on boundary-layer transition on a flat plate. The tests were performed at a nominal Mach number of 2.40 and a free-stream temperature of 205 deg F, and the data were obtained at nominal plate temperature levels of 60 deg (adiabatic recovery temperature), 100 deg, 140 deg, 180 deg, and 260 deg F over a length Reynolds number range from 0.475 x 10(exp 6) to 3.93 x 10(exp 6). The identification of the onset and end of transition was made by inspection of the curves of surface-tube Mach number reading as a function of length Reynolds number obtained through the transition region. Boundary-layer-velocity profiles were obtained at points corresponding to the onset and end of transition to enable the computation of critical Reynolds numbers based on boundary-layer dimensions.

Descriptors :   *SUPERSONIC FLOW, *BOUNDARY LAYER TRANSITION, *SURFACE TEMPERATURE, REYNOLDS NUMBER, FLAT PLATE MODELS.

Subject Categories : FLUID MECHANICS

Distribution Statement : APPROVED FOR PUBLIC RELEASE

Search DTIC's Public STINET for similiar documents.

Members of the public may purchase hardcopy documents from the National Technical Information Service.