BOUNDARY-LAYER, PRESSURE, AND TEMPERATURE DISTRIBUTION STUDIES ON SEVERAL ISENTROPIC COMPRESSION SURFACES AT MACH NUMBERS FROM 4 TO 8

Abstract

Boundary-layer, pressure, and temperature measurements were obtained on the generating cylinder and isentropic compression surface of several axisymmetric hypersonic inlet configurations at supersonic and hypersonic Mach numbers. Boundary-layer surveys were performed at selected stations on uncooled Mach 5, 6, and 10 inlets and a cooled Mach 8 inlet. Model surface temperatures and pressures were obtained at several Mach numbers on all configurations. Steady-state heat transfer data were obtained on the Mach 8 inlet at several model wall temperatures. Selected results from the tests are presented.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1964
Accession Number
AD0453217

Entities

People

  • F. K. Hube
  • R. W. Rhudy

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Compression
  • Data Reduction
  • Free Stream
  • Geometry
  • Heat Transfer
  • Instrumentation
  • Layers
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Static Pressure
  • Surface Temperature
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

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