Mach Tables for Real Gas Equilibrium Flow of Air In Hypervelocity Test Facilities with Total Temperatures to 10,000 deg K
SANDIA CORP ALBUQUERQUE NM
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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.
- Fluid Mechanics