| Summary: | 碩士 === 國防大學理工學院 === 航空太空工程碩士班 === 100 === In this study the simulation of forebody of interceptor through rarefied hypersonic gas flow at high altitude is taken for understanding the aerothermodynamic and aero-optic effects outside of the optical window. Wish to provide the reference data for the defense weapons R & D personnel.
Research process is divided into the flow field simulation and the aero-optical analysis. First to obtain two-dimensional wedge oblique shock velocity by shock wave theory, then simplify the model into two-dimensional shallow cavity and use Direct Simulation Monte Carlo for simulation of flow field at different heights (60km, 80km, 100km). Subsequently jet flow is injected in the left side of the shallow cavity to simulate with the same conditions and compare the heat insulation effects of the jet. From the simulated flow field density distribution, the flow field can be simplified and roughly divided into three density interval. After individually derived its average density, the diplacement of image can be calculated from different incident angle (15°,30°, 45°,60°,75°) with Snell's Law and specific refractivity (Gladstone-Dale relation) for optical images analysis.
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