Heat-Transfer Investigation of Langley Research Center Delta Wing Configurations at Mach Numbers 8 and 10.5

Abstract

Heat-transfer tests for two simple delta wing configurations submitted by NASA-Langley Research Center were conducted at Mach numbers 8 and 10.5. Test conditions provided both Mach number and Reynolds number simulation for typical lifting body reentry trajectories. This report presents the major test results and comparisons with theoretical calculations. Specific test results include heat-transfer distributions, shock angles, limited pressure measurements, and boundary-layer transition results.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1973
Accession Number
AD0755355

Entities

People

  • R. H. Eaves
  • R. K. Matthews
  • T. D. Buchanan

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Layer Transition
  • Cameras
  • Electric Arcs
  • Engineering
  • Heat Transfer
  • Heat Transfer Coefficients
  • Isotherms
  • Mach Number
  • Measurement
  • Photographs
  • Pressure Distribution
  • Pressure Measurement
  • Surface Roughness
  • Test Facilities
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.