발사체 기저 유동 해석을 위한 2-방정식 난류 모델의 압축성 보정

다국어 초록 (Multilingual Abstract)

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 κ-ω 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.