WALL COOLING EFFECTS ON AXISYMMETRIC LAMINAR REATTACHING FLOWS AT HYPERSONIC SPEEDS

Abstract

A flared (10-deg semiangle) axisymmetric body was tested at Mach 6, 8, and 10 in the von Karman Gas Dynamics Facility to investigate the effect of model wall temperature on the existence of laminar flow separation and reattachment. The results consisted of longitudinal surface pressure distributions obtained at zero incidence. By varying the stagnation pressure, the influence of the free-stream Reynolds number on the extent of flow separation was also investigated. Extensive measurements were made at Mach 8 for Reynolds numbers (based on centerbody diameter) ranging from about 0.05 to 0.29 million and at wall temperatures from about 0.1 to 0.8 times the free- stream stagnation temperature.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1968
Accession Number
AD0677589

Entities

People

  • J. D. Gray

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Flow
  • Flow Separation
  • Fluid Dynamics
  • Free Stream
  • Geometry
  • Laminar Flow
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Stagnation Pressure
  • Stagnation Temperature
  • Temperature Gradients
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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