Supersonic and Hypersonic Aerodynamic Characteristics of Two Shuttle-Orbiter Configurations Designed for Reduced Length

Abstract

Performance, stability, and control tests at supersonic and hypersonic speeds have been performed on two versions of a shuttle orbiter configuration designed for reduced length. One of the test configurations had twin dorsal fins rolled out 15 deg, the other a centerline single dorsal fin. Effects of eleven and body flap deflection, rudder flare, planform fillet, and aileron deflection were examined. The supersonic tests were over the Mach number range from 1.6 to 4.63 at a Reynolds number based on model length of 4.3 x 10(exp 6). The hypersonic tests were conducted at a Mach number of 10.3 and Reynolds number of 0.67 x 10(exp 6). Aerodynamics, Supersonic and hypersonic, Space vehicles.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1974
Accession Number
ADA279440

Entities

People

  • Howard W. Stone

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerospace Industry
  • Aspect Ratio
  • Center Of Gravity
  • Coefficients
  • Deflection
  • Dynamic Pressure
  • Leading Edges
  • Mach Number
  • Planform
  • Reynolds Number
  • Rocket Engines
  • Rockets
  • Scale Models
  • Trailing Edges
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

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