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研究了在锥型喷管和理想喷管过膨胀射流中激波后的参数控制问题。通过采用УсковВ.Н所给出的微分动力学相容性条件,得到了激波后气动参数沿激波分布的计算方法。该方法所得到的计算结果与实验结果是一致的。这一方法可用于指导某些气动装置的设计。
The problem of parameter control after shock waves in coning nozzle and ideal nozzle over-expansion jet was studied. By using the differential dynamic compatibility conditions given by УсковВ.Н, the method for calculating the aerodynamic parameters along the shock wave distribution is obtained. The calculation results obtained by this method are consistent with the experimental results. This method can be used to guide the design of certain pneumatic devices.