The hammer shock load caused by the transient high pressure induced by engine surge is one of the key factors in the aircraft inlet structural strength design.Through the unsteady numerical calculation of the integrated internal and external flow of the aircraft,the evolution process of the unsteady three-dimensional flow field of the internal hammershock wave in the double S-bend inlet was analyzed,and the influence of different Mach number and overpressure ratio on the inlet hammer shock wave load of the inlet hammer was studied.The results show that when the hammer shock wave passes through the inlet curve,the pressure of the flow field on the outside of the curve is much greater than that on the inside.After the hammer shock wave leaves the inlet,the flow field in the inlet gradually returns to the initial state after several cycles.When the inlet pressure is the same,the smaller the incoming Mach number is,the faster hammer shock wave propagates in the inlet,and the larger the peak value of the inlet pressure coefficient is.Under the same inlet Mach number,with the increase of the overpressure ratio,the faster the hammer shock wave propagates in the inlet,the larger the peak value of the pressure coefficient in the inlet.
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