Pressure and Heat Transfer Tests on the NASA Space Shuttle External Tank at Mach Number 16

Abstract

An experimental test program was conducted in the AEDC-VKF Hypervelocity Wind Tunnel (F) at a nominal Mach number of 16 to obtain basic heating and pressure distribution data on the NASA Space Shuttle external tank. The tests were conducted over an attitude range which simulated tank tumbling after separation from the Shuttle orbiter. The angles of attack varied from 0 to -180 deg with combinations of roll from 0 to 90 deg at free-stream Reynolds numbers (based on model length) from 0.38 x 1,000,000 to 1.10 x 1,000,000. In addition to surface heat-transfer gages, thermographic phosphor paint was used to determine the interference heating factors on and around the various attachment structures and service ducts.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1975
Accession Number
ADA015743

Entities

People

  • A. H. Boudreau
  • L. G. Siler

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Data Acquisition
  • Data Analysis
  • Electric Arcs
  • Engineering
  • Free Stream
  • Heat Transfer
  • Instrumentation
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gages
  • Pressure Measurement
  • Reynolds Number
  • Space Flight
  • Strain Gages
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers