발사체 기저 유동 해석을 위한 2-방정식 난류 모델의 압축성 보정

초록

Explicit compressibility correction methods have been applied to two-equation RANS turbulence models for analyzing the base flow and the entire flow field of a projectile. First, supersonic base flow at a specific Mach number has been analyzed to compare performances of the various compressibility corrections. Base flows at various Mach numbers and Reynolds numbers with Ristorcelli’s compressibility correction applied to SST model have been computed, and compared with the experimental results. Lastly, transonic flow analyses of a secant-ogive-cylinder projectile have been performed with Ristorcelli’s compressibility correction. It is found that Ristorcelli’s compressibility correction gives considerable improvement in predicting the base pressure and drag at various flow conditions.

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