Heat Transfer Test on the NASA/Rockwell International Space Shuttle Orbiter at Mach number 8.0 in AEDC/VKF Tunnel B

Abstract

Heat-transfer data were obtained on a 0.0175-scale and on a 0.04- scale model of the NASA/Rockwell International Space Shuttle Orbiter. The data were obtained at mach 8 in the AEDC/VKF Tunnel B at angles of attack from 25 to 42.5 deg and at several free-stream Reynolds numbers from 500,000 to 3,700,000 per ft.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1978
Accession Number
ADA059497

Entities

People

  • E. C. Knox

Organizations

  • Arnold Engineering Development Complex

Tags

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Fineness Ratio
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Leading Edges
  • Mach Number
  • Measurement
  • Photography
  • Reynolds Number
  • Scale Models
  • Space Shuttles
  • Test And Evaluation
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster