EFFECTS OF PARALLEL-JET MIXING ON DOWNSTREAM MACH NUMBER AND STAGNATION PRESSURE WITH APPLICATION TO ENGINE TESTING IN SUPERSONIC TUNNELS

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1953
Accession Number
AD0005152

Entities

People

  • Harry Bernstein

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Back Pressure
  • Boundary Layer
  • Combustion
  • Combustion Chambers
  • Engines
  • Exhaust Gases
  • Flow
  • Flow Rate
  • Free Stream
  • Gas Flow
  • Mach Number
  • Mass Flow
  • Stagnation Pressure
  • Static Pressure
  • Supersonic Wind Tunnels
  • Thermodynamic Properties
  • Wind Tunnels

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow