Missile Supersonic Inlet Design, Numerical Simulation And Flow Control Research

According to the characteristics of a supersonic cruising missile's inlet, the designed Mach number of which is 4.0, a mixed-compression supersonic axisymmetric ramjet inlet is adopted in this paper. The design characteristics and requirements are analyzed. The design method is presented, according to which an optimization programmer has been obtained. And the programmer can be applied to this kind of inlets. The design of the cowl, which has not been researched domestically, is a linchpin and a difficulty to the design of this kind of inlets. And in this paper, the cowl is designed by way of estimation and revision after the numerical simulation. The geometric parameters of the inlet are gained by using the programmer, according to the design requirements. Then the inlet model is set up, and the grid of the research region is gained. Finally the flow fields and the interrelated parameters of different flight Mach numbers and different exit pressures are obtained after the numerical simulation with commercial software, using the standard k-ε, k-ω turbulence models and the Reynolds-averaged Navier-Stokes equations. It is obtained that the characteristics and the varying disciplinarians of the flow field and the total pressure recovery, the Mach number and the temperature at the exit of the inlet as the varying of the flight Mach number and the exit pressure. Moreover, the causations of the characteristics and the disciplinarians are analyzed.What can be discovered is that, because of the shock wave/boundary-layer interaction, there is serious flow separation near the underside wall of the inlet's inner channel, when the flight Mach number is higher. And the separation will be severer while the flight Mach number is higher, especially at the design Mach number. Moreover, the characteristics and the causes of the flow separation are analyzed. The flow separation results in the serious reduction of the total pressure recovery and the serious increase of the distortion, which leads to the badly dropping of the inlet's performance. So the control against the flow separation is necessary.Because there is more serious flow separation near the underside wall than the upside wall of the inlet's inner channel, so some slots are opened on the underside wall of the expanded sect. And these slots are used to remove the low-momentum fluid near the wall to reduce the thickness of the boundary layer, which is the theory of this method for the flow separation control. Flow fields of different slot positions, upriver, downriver and near the separation point, and different bleed mass flow are...