LAMINAR SEPARATION IN SUPERSONIC FLOW

Abstract

A preliminary experimental investigation was made of the effect of three-dimensional flow perturbations on the heat-transfer rate in the reattachment region of a laminar flow behind a two-dimensional backward-facing step. It was found that the mean value of the heat-transfer rate was increased by as much as 70% by the presence of strong flow perturbations, while the recovery factor increased approximately from the laminar value to the turbulent one. A novel technique of heat-transfer measurements was used, by which heat was uniformly dissipated on the surface of the model. A theory was developed for the case of a supersonic flow over a flat plate, which gives an exact solution of the boundary-layer equations when heat is uniformly dissipated on the surface. It was shown in particular that the ratio of the heat-transfer coefficient for an isothermal wall to the heattransfer coefficient for uniform heat-flux is a constant independent of Mach number and Reynolds number. Numerical integration showed that it is equal to 0.72, independently of the Prandtl number in the range 0.5 to 1.0. (Author)

Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1962
Accession Number
AD0292901

Entities

People

  • Jean J. Ginoux

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Flow
  • Heat Flux
  • Heat Transfer
  • Heat Transfer Coefficients
  • Laminar Flow
  • Mach Number
  • Numerical Integration
  • Prandtl Number
  • Reynolds Number
  • Supersonic Flow
  • Three Dimensional
  • Three Dimensional Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers