超声速进气道数学模型研究

Study for the mathematical model of supersonic inlet

应用数值模拟方法对二级斜板可调的二元混压式超声速进气道的内流场性能进行了研究,根据数值模拟二元混压式超声速进气道内流场的计算结果,得出每个网格点上的压力、温度、速度及密度等参数,从而求出进气道的总压恢复系数和流量系数,并归纳出进气道主要性能参数与状态参数和几何调节参数之间的关系,得出进气道的特性曲线,建立了二元超声速进气道的数学模型。利用此数学模型,可确定进气道在不同状态下的主要内特性参数值,并作为建立带进气道、矢量喷管的发动机数学模型的建模基础,对进气道、发动机、矢量喷管的一体化控制有重要的参考价值。

Applying the numerical simulation method, the inner flow field performance was studied in a 2-D ex-internal compression supersonic inlet. On the basis of these numerical simulations, the parameters including pressure, temperature, velocity and density in every grid were gotten, and then the total pressure recovery coefficient and flow rate coefficient were calculated. The relations of these parameters and correlating state and geometry parameters were concluded and the inlet mathematical model was established. According to the model, main inner performance parameters under the different conditions can be determined. This model is the basis for researching the engine mathematical model with supersonic inlet and integrated flight/propulsion system control.