Experimental Study on Shock Train Characteristics in Concave Channels
The three-dimensional internal rotating inlet has become the development trend of future hypersonic inlets due to its advantages such as high total pressure recovery coefficient and high compression efficiency.However,the more complex shock train structure and shock train/boundary layer interaction in the flow field of an internal rotating inlet be-come key constraints on its performance.In response to the complex flow characteristics in an internal rotating inlet,hy-personic ground wind tunnel experiments are conducted and measurements of the flow field are visualized.Firstly,a su-personic direct connected wind tunnel experimental platform is built;secondly,a square to circular section is designed to smoothly connect the unique concave channel and rectangular nozzle in the inner rotating inlet.The final results indicate that the shock wave at the leading edge of the shock train in the concave channel is of type"λ"at low Mach numbers and of type"X"at high Mach numbers,and large flow separation occurs on the flat wall side,resulting in significant asymme-try in the flow field.In addition,as the back pressure increases,the shock wave train continues to move forward,and the pressure at the measurement point where the leading edge shock wave reaches undergoes a significant oscillation jump.
internal rotating inletconcave channelshock trainshock train leading edge
万方数据
维普
