Inverse Design Of Hypersonic Air Compression Tube For Generating Desirable Mach Profile

The majority works of the aerodynamic inverse design focus on shape determination base on given wall parameter profile(pressure\Ma etc.). In addition to providing the compressed air with proper thermodynamic parameters to the scramjet burner, the inlet must also provide desirable flow conditions. There are few researches have covered the inverse design of hypersonic compression airflow tube given the inlet\outlet velocity profile. For the above reasons, based on the Method of Characteristic(MOC), the author investigated the inverse design method which could yield hypersonic airflow compression tube that give desirable Mach profile at the outlet.The configuration of the shockwave system and corresponding curve compression surface generation were investigated. The supersonic flow field assemble technique was described in detail. A kind of shockwave system which involve two curve shockwaves to realize the given Mach profile at the outlet was proposed. By using this method, a uniform mach profile to a desirable Non-uniform Mach profile, a non-uniform Mach profile to a desirable uniform Mach profile and a uniform mach profile to a desirable uniform Mach profile were realized successfully. A new kind of hypersonic inlet which could generate desirable Ma profile at the outlet was designed in this thesis by utilizing this method. The method which base on MOC was verified through CFD simulation. A hypersonic wind tunnel test was designed in this thesis. The test model was designed using this method. The experimental result showed that the Mach profile of the core flow fits the desirable profile well, which means the method is very sound. The author also explored the method to generate3D Mach distribution at the outlet by employing Slice Stacking Technique(SST). Currently, the SST is widely used in axial compressor or turbine blade design.