Accession Number : AD0030435


Title :   PERFORMANCE OF WEDGE-TYPE BOUNDARY-LAYER DIVERTERS FOR SIDE INLETS AT SUPERSONIC SPEEDS


Descriptive Note : Research memo.


Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH GLENN RESEARCH CENTER


Personal Author(s) : Campbell, Robert C ; Kremzier, Emil J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/030435.pdf


Report Date : 13 May 1954


Pagination or Media Count : 26


Abstract : An experimental investigation to determine the effect of several wedge-type boundary-layer diverters on drag and inlet pressure recovery has been conducted in the Lewis 8- by 6-foot supersonic-wind tunnel at free-stream Mach numbers of 1.5, 1.8, and 2.0. The model investigated consisted of two rectangular ramp-type inlets mounted on the NACA RM-lO body of revolution. 0 0 Results indicated that for wedges of 60 and 100 included angle, inlet-body drag was 9 to 15 percent higher than for wedges of 160 included angle. Since increases in diverter wedge angle increased the model drag with some decrease in inlet pressure recovery for the higher angles in their forward position, it appears aerodynamically desirable to keep the diverter included angle at or near 160. Ducted wedges showed increases in drag over most of the comparable closed-wedge configurations and an increase in pressure recovery over comparable closed-wedge diverters at the inlet ramp leading edge.


Descriptors :   *BOUNDARY LAYER , *WEDGES , *SUPERSONIC INLETS , *DUCT INLETS , INSTRUMENTATION , LEADING EDGES , BOUNDARY LAYER CONTROL , FREE STREAM , MACH NUMBER , SUPERSONIC FLOW


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE