Accession Number:

AD0602360

Title:

SEPARATION AND REATTACHMENT OF SUPERSONIC TURBULENT BOUNDARY LAYER BEHIND DOWN STREAM FACING STEPS AND OVER CAVITIES,

Descriptive Note:

Corporate Author:

DOUGLAS AIRCRAFT CO INC SANTA MONICA CALIF

Personal Author(s):

Report Date:

1964-03-01

Pagination or Media Count:

180.0

Abstract:

Surface pressure measurements were obtained for the flow regimes created when a turbulent boundary layer in supersonic flow separates over the classical downstream-facing step and over a cavity. The experiments were conducted in the Mach number range 2.0 to 4.0 on a model having a ducted, one-foot diameter, axisymmetric body. The model provided step heights of 0.250, 1.020, and 1.675 inches, cavity lengths of 0.837 and 1.675 inches, and a cavity depth of 1.675 inches. The recompression shoulder of the cavity had either a square or a rounded shape. In general, the pressure rise at reattachment is found to be in good agreement with Korsts theory. The shape and scale of the reattachment pressure distribution are influenced considerably by Mach number. Reattachment occurs at a point where the pressure rise is about 50 complete. A point of flow reversal is found to be located upstream of the reattachment point. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE