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 Navier-Stokes 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;
- Navier-Stokes Equation;
- Thrust Chambers;
- Vacuum Tests;
- Wind Tunnel Tests;
- Fluid Mechanics and Heat Transfer