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김재관(J. G. Kim),이준우(J. W. Lee),김규홍(K. H. Kim) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
Numerical investigation was conducted to study the effects of after-body configurations and nozzle lip on the PIFS(Plume Induced Flow Separation) and heat flux to the base face. Two dimensional and axi-symmetric non-equilibrium Navier-Stokes solver with k-ω SST turbulence model was used to solve the launching vehicle type configuration with propulsive jet. The experimental result of Robert J. McGhee was compared with our computational results for code validation. Three types of the after-body configurations (Straight, Boat-tail, Flare type) were simulated for this study. And the nozzle lip effect was studies using the three types of base configurations with same simulation conditions. As a result of numerical investigations, higher pressure ratio condition and boat-tail after-body configuration caused severe PIFS phenomenon but the flare type after-body configuration and low pressure ratio suppressed PIFS. Flare type after-body configuration and low pressure ratio case reduced heat flux to base face. The nozzle lip dispersed the heat flux widely along the base face and the nozzle lip.
김재관(J.G. Kim),이준우(J.W. Lee),김규홍(K.H. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
Numerical investigation was conducted to study the effects of after-body configurations and altitude conditions on the PIFS (Plume Induced Flow Separation) and heat flux to the base face. Two dimensional and axi-symmetric Navier-Stokes solver with k-w SST turbulence model was used to solve the various configuration with propulsive jet. The cylinder, boat-tail and flare after-body configurations and six different altitude conditions (5, 10, 20, 30, 40, 50Km) are used in this study. As a result of numerical investigations, higher pressure ratio condition and boat-tail after-body configuration caused severe PIFS phenomenon but the flare type after-body configuration suppressed PIFS. Flare type after-body configuration reduced heat flux to base face.
압력 조건과 기저 온도 조건에 따른 기저 열전달률 계산
김재관(J.G. Kim),이준우(J.W. Lee),최중근(J.K. Choi),김규홍(K.H. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
Numerical study was conducted to simulate the heat transfer on the real launch vehicle base. Three different base temperatures were chosen, to simulate the heat accumulation on the base. Moreover, six different pressure ratio conditions were used to express the different air conditions. As a result, the table that can used to estimate the base heat flux along the base temperature and pressure condition was made.