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

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)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1966
Accession Number
AD0634282

Entities

People

  • William H. Miller

Tags

DTIC Thesaurus Topics

  • Adiabatic Conditions
  • Air Flow
  • Boundary Layer
  • Bow Shock
  • Flow
  • Flow Fields
  • Free Stream
  • Layers
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Shock
  • Turbulent Boundary Layer
  • Turbulent Mixing

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow