Accession Number : AD0634282

Title :   PRESSURE DISTRIBUTIONS ON SINGLE AND TANDEM CYLINDERS MOUNTED ON A PLATE IN MACH NUMBER 5.0 FLOW.

Descriptive Note : Technical rept.,

Corporate Author : DEFENSE RESEARCH LAB UNIV OF TEXAS AUSTIN

Personal Author(s) : Miller, William H.

Report Date : 01 JUN 1966

Pagination or Media Count : 80

Abstract : The distributions of pressures on short, circular cylinders mounted perpendicular to a flat surface and protruding into a supersonic air flow were determined. Schlieren photographs of the associated flow fields supplemented these data. Tests were conducted under adiabatic conditions with a free-stream Mach Number of 4.88 and a Reynolds Number of 576,000. Protuberance heights ranging from 0.23 to 6 times the local thickness of the turbulent boundary layer on the supporting surface were investigated. Upstream, shear-layer separation occurred. An oblique compression zone accompanied this separation and intersected the protuberance bow shock to form a lambda shock. High values of pressure recovery and sectional drag were indicative of this region of shock interaction. The model pressure loadingin certain tandem configurations was found to exceed the corresponding local single-cylinder values. Form-drag coefficients, determined by graphical integration of the pressure data, correlated well with total drag coefficients reported in the literature. (Author)

Descriptors :   (*CYLINDRICAL BODIES, PRESSURE), (*HYPERSONIC FLOW, CYLINDRICAL BODIES), DISTRIBUTION, FLAT PLATE MODELS, SUPERSONIC FLOW, ADIABATIC GAS FLOW, TWO DIMENSIONAL FLOW, SHEAR STRESSES, DRAG

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE