Numerical solutions of full Navier-Stokes equations with chemical reaction flow were established for the nozzle flow of the LOX/HTPB hybrid rocket motor.

• 利用二维轴对称N-S方程和组分方程对选用液氧/端羟基聚丁二烯推进剂的固液混合火箭发动机喷管流动进行了计算。