Test Results from the NASA/Rockwell International Space Shuttle Integrated Vehicle Test (IH 85) Conducted in the AEDC-VKF Tunnel A.

Abstract

Tests were conducted to obtain convective heat-transfer-rate distributions on the Space Shuttle Integrated Vehicle during simulated first and second stage conditions of the flight profile. The test model was a 0.0175-scale model (60-OTS). Model configurations tested included the Integrated Vehicle and the Orbiter/External Tank with the Solid Rocket Boosters removed. The tests were conducted at Mach numbers 3 and 4 using the thin-skin thermocouple technique. The model was tested at angles of attack of 0, + or - 2.5, and + or - 5 deg and at yaw angles of 0, + or - 3, + or - 4.5, + or - 5, + or - 7.5, and + or - 9 deg. A test description is presented.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1978
Accession Number
ADA058141

Entities

People

  • Kenneth W. Nutt

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Booster Rocket Engines
  • Boundary Layer
  • Calibration
  • Coefficients
  • Data Reduction
  • Flow
  • Free Stream
  • Heat Transfer
  • Mach Number
  • Measurement
  • Nose Tips
  • Space Shuttles
  • Supersonic Wind Tunnels
  • Test And Evaluation
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Fluid Dynamics.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster