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介绍了模拟零攻角时固体燃料冲压发动机导弹超音速飞行的计算机程序。该程序利用实验阻力数据计算射程和飞行速度与时间的关系，先计算气流经过锥形附体激波后的变化。在此激波下游，超音速气流进入进气道，穿过正激波到达燃烧室。在燃烧室中，借壁蒸发作用加入燃料。假设燃烧产物达到化学平衡，同时假设在燃烧室每个横截面都反应充分。燃烧室化学反应使其流体总温、马赫数的总压产生变化。流体离开燃烧室经节流喷管而存在，根据几何参数确定所完成的行程
The computer program for simulating the supersonic flight of a solid fuel ramjet missile simulating zero angle of attack is introduced. The program uses experimental resistance data to calculate the range and flight speed versus time, and then calculates the change in air flow past the conformal enclosure shock. Downstream of this shock, supersonic airflow enters the intake duct and across the forward shock to the combustion chamber. In the combustion chamber, fuel is added by wall evaporation. It is assumed that the products of combustion reach a chemical equilibrium, while assuming sufficient reaction at each cross-section of the combustion chamber. Combustion chamber chemical reaction to the total fluid temperature, Mach number of the total pressure change. Fluid leaving the combustion chamber through the throttle nozzle exists, according to the geometry to determine the completion of the trip