THE ASYMMETRIC ADJUSTABLE SUPERSONIC NOZZLE FOR WIND-TUNNEL APPLICATION

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1953
Accession Number
AD0005155

Entities

People

  • H. J. Allen

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Boundary Layer
  • Boundary Layer Control
  • Compression Ratio
  • Curvature
  • Flow
  • Geometry
  • Mach Number
  • Pressure Gradients
  • Pressure Measurement
  • Shape
  • Shock Waves
  • Supersonic Flow
  • Supersonic Nozzles
  • Supersonic Wind Tunnels
  • Two Dimensional
  • Wind Tunnels

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow