Computation of supersonic, reacting flow in an MPD vacuum test chamber
Abstract
This paper presents a program system for computing supersonic reacting flows in an MPD vacuum test chamber of a plasma wind tunnel. The program system is divided into three parts: a NavierStokes flow field solver, a solution program of the electron energy equation yielding the electron temperature, and a code for the evaluation of the species conservation equations. Two example cases are presented, one for calculating a low expansion ratio, the other for a high expansion ratio.
 Publication:

AIAA, DGLR, and JSASS, 21st International Electric Propulsion Conference
 Pub Date:
 July 1990
 Bibcode:
 1990iep..confS....G
 Keywords:

 Arc Jet Engines;
 Combustible Flow;
 Computational Fluid Dynamics;
 Magnetoplasmadynamics;
 Supersonic Flow;
 Vacuum Chambers;
 Flow Distribution;
 NavierStokes Equation;
 Thrust Chambers;
 Vacuum Tests;
 Wind Tunnel Tests;
 Fluid Mechanics and Heat Transfer