Investigation On Design Methodology For Inward Turning Inlet Based On The Rotational Method Of Characteristics

As the technique of hypersonic propulsion becomes more and more sophisticated,Hypersonic inward turning inlet becomes popular because of its excellent performance.The key of design hypersonic inward turning inlet is designing its base flowfield. In thispaper, using the rotational method of characteristics, a design method of Dual-ShockWave base flowfield for inward turning inlet is presented. This kind of base flowfieldhas a leading edge shock wave due to its initial turn angle at the leading edge. Theending shock wave collide on the shoulder and there is no shock wave reflection at theshoulder.Based on the rotational method of characteristics,the base flowfield design can bedivided into four sub-flowfield.they can be called leading edge shock wave dependentfield, main isentropic compression field, ending shock wave dependent field, stabilizefield. In the leading edge shock wave dependent field, the initial turn angle and thestrength of the leading edge shock wave can be controlled.Isentropic compression lawcan be controlled by the main isentropic compression field. In the ending shock wavedependent field, we can eliminate the reflection of the ending shock wave at theshoulder through the constitution of the ending shock wave.The flow can be more andmore uniform while it flow through the stabilize field.Using the streamlinetraced method, an arbitrary entrance shape of streamlinetracedinlet can be realized. The applicability of the streamlinetraced method is verifiedthrough the Numerical Simulasion. According to the result, the performance andflowfield structure of the streamlined inlet inherit the base flowfield well. The crosswisepressure gradient does not have any influence in the Streamlinetraced inlet.Through the cross sectional shape generating method of Hypersonic inlet design, Arectangular entrance to circular exit inward turning inlet is designed. According to theNumerical Simulation result, the inlet designed via the method has a mass capture ratioas high as0.94. The performance of the inlet inherit the streamlinetraced inlet well to agreat extent.