Mach Tables for Real Gas Equilibrium Flow of Air In Hypervelocity Test Facilities with Total Temperatures to 10,000 deg K

Abstract

Aerodynamic flow parameters for isentropic expansions and flow through normal shocks, including real gas effects, have been calculated for total temperatures of 4000 to 10,000 deg K and for total pressures of 100 to 4000 atmospheres. Calculations assume equilibrium flow. Results indicate real gas effects vary from a few percent to more than two orders of magnitude.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1961
Accession Number
AD0262842

Entities

People

  • K. L. Goin

Tags

Communities of Interest

  • C4I
  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Air Temperature
  • Compressive Properties
  • Dynamic Pressure
  • Energy Conversion
  • Enthalpy
  • Equations
  • Gas Flow
  • Heat Energy
  • Low Temperature
  • Mach Number
  • Nozzles
  • Standards
  • Static Pressure
  • Test Facilities
  • Thermodynamic Properties
  • Wind Tunnel Nozzles
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Combustion and Flow Dynamics.
  • Combustion science or combustion engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight
  • Hypersonics - Hypersonic Flow