Supersonic Inlet Flow Inside And Outside The Field Of Computing And Mathematical Model Study

With the development of the modern science and technology, higher requests have been put forward to the new advanced aircraft. To meet these requests, the integrated flight/propulsion system control technology must be applied, one of the important research work of which is to establish the mathematical model of the inlet.The main performance parameters of 2-D ex-internal compression supersonic inlet have been calculated by means of the numerical simulation method, then the relations of these parameters and some factors, such as flight condition, geometric configuration parameters have been analyzed and summarized in this paper. On the basis of these results, the relations of total-pressure recovery coefficient or flow coefficient and flight mach number, angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting, then the mathematical model of the inlet is established. Information about this new method by means of the numerical simulation method to set up the model of the inlet hasn't been reported so far at home or abroad. This paper has provided a feasible approach.The research work as the exploratory study, which has been done provides a base for the next study of integrated propulsion system control.