MEASUREMENT OF THE HEAT TRANSFER TO A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY.

Abstract

The report describes the experimental measurement of aerodynamic heat transfer to a two-dimensional variable geometry hypersonic inlet model. The program was conducted in a twenty-inch hypersonic tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds numbers of 721,000 and 631,000 per foot. The experimental results are compared to an approximate theoretical solution for laminar boundary layer flow over a flat plate. (Author)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1965
Accession Number
AD0625095

Entities

People

  • James D. Mcdonel
  • Widen Tabakoff

Organizations

  • University of Cincinnati

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Flow
  • Flow
  • Free Stream
  • Geometry
  • Heat Transfer
  • Laminar Boundary Layer
  • Layers
  • Mach Number
  • Measurement
  • Reynolds Number
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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