Force and Moment Tests to Determine the Interaction Effects of the Reaction Control System Jet Plumes on the Space Shuttle Orbiter Aerodynamics at Mach Number 6 (Test 0A352)

Abstract

The purpose of this wind tunnel test was to expand the existing Space Shuttle aerodynamics and reaction control system (RCS) data base to support the Glide Return to Launch Site (GRTLS) abort trajectory and the new Digital Autopilot. An existing model of the orbiter was used to investigate the aerodynamic effects of several combinations of RCS thrusters and thruster momentum ratios at Mach number 6. Two separate model installations were used to achieve an angle of attack range of -11 to 46 deg. The test was conducted at a unit Reynolds number of 800,000 per foot. Keywords: Hypersonic characteristics; Space shuttle orbiter; Aerodynamic interference.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1987
Accession Number
ADA189391

Entities

People

  • Robert W. Cayse

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms
  • Cyber
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Aerodynamics
  • Air Force
  • Air Supplies
  • Control Systems
  • Data Reduction
  • Databases
  • Engineering
  • Flow Rate
  • Fluid Dynamics
  • Free Stream
  • Hypersonic Wind Tunnels
  • Instrumentation
  • Mach Number
  • Measurement
  • Reynolds Number
  • Security
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering.

Technology Areas

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