Abstract: Burning gas jet flow fields generated by φ21 and φ9 rocket motor have been investigated both numerically and experimentally. In calculation, a high resolution, second accuracy for shock wave TVD scheme is employed. Clear maps corresponding to the flow fields which include jet boundary, barrel shock, reflected shock, Mach disk and slip line have been obtained. In experimental measurement, F P laser interferometry and auto measurement system are used to take F P interference pictures and test pressure distributions. The computed results are in agreement with the experimental data.

Key words: gas streams, numerical, analysis TVD schemes, laser interferometry