A Direct Comparison of Reentry F Heat-Transfer-Rate Data to Ground Facility Measurements

Abstract

Correlation parameters are developed to compare ground test facility surface heating-rate data on non-ablating sharp slender cones directly to data obtained during a full-scale hypersonic reentry flight. Surface data under laminar and fully developed turbulent boundary layers are compared. The problem of failure to fully simulate local Mach number, Reynolds number, and boundary- layer temperature is shown to be of secondary importance. Sufficient information is provided to allow the reader to add additional experimental results.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1974
Accession Number
ADC000236

Entities

People

  • David E. Boylan

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Boundary Layer Transition
  • Flow Fields
  • Fluid Dynamics
  • Fluid Mechanics
  • Heat Transfer
  • Layers
  • Mach Number
  • Measurement
  • Physics Laboratories
  • Reynolds Number
  • Statistical Analysis
  • Test Facilities
  • Turbulent Boundary Layer
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.
  • Systems Analysis and Design

Technology Areas

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