PRESSURE RECOVERY MEASUREMENTS ACROSS A TWO-DIMENSIONAL HYPERSONIC INLET WITH VARIABLE GEOMETRY.

Abstract

The report describes the experimental measurement of pressure recovery across a simulated combustion chamber duct of a two-dimensional hypersonic inlet with variable geometry. The model tested was a wedge type inlet which generated a single external shock wave. The program was conducted in the twenty-inch hypersonic wind tunnel. Testing was at a nominal free stream Mach number of 14 and free stream Reynolds number of 721,000 per foot. (Author)

Document Details

Document Type
Technical Report
Publication Date
May 01, 1965
Accession Number
AD0617620

Entities

People

  • James D. Mcdonel
  • Widen Tabakoff

Organizations

  • University of Cincinnati

Tags

DTIC Thesaurus Topics

  • Chambers
  • Combustion
  • Combustion Chambers
  • Free Stream
  • Geometry
  • Hypersonic Wind Tunnels
  • Mach Number
  • Measurement
  • Recovery
  • Reynolds Number
  • Shock Waves
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow