AN EXPERIMENTAL METHOD FOR DETERMINING HEAT TRANSFER DISTRIBUTIONS ON BLUNT BODIES AT HYPERSONIC MACH NUMBERS

Abstract

Experimental convective heat transfer distributions on a hemisphere- cylinder configuration were obtained using slug calorimeters and Gardon gages. Wind tunnel tests were conducted at a nominal Mach number of 10 over a free- stream Reynolds number range from 310,000 to 1,040,000 based on the model diameter (5.80 inches). The data were compared with theoretical heat transfer values and data obtained with thin-skin calorimetric wind tunnel models. The slug calorimeter data were highly time dependent due to conduction heat losses; consequently, the data did not compare favorably with theoretical predictions. Gardon gage indicated heat transfer was in very good agreement with both theoretical values and data from other sources.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1969
Accession Number
AD0689176

Entities

People

  • Frederick Karl Hube

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Bodies
  • Boundary Layer
  • Data Reduction
  • Free Stream
  • Heat Loss
  • Heat Transfer
  • Heat Transfer Coefficients
  • Jet Propulsion
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Reynolds Number
  • Temperature Gradients
  • Thermal Diffusivity
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Readers

  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow