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VOC 제거효율 향상을 위한 실리콘복합막(SR-PSf) 제조에 관한 연구
권창오 김천대학교 2002 김천대학교 논문집 Vol.23 No.-
In this study, silicon rubber(SR) dense membrane was made from room temperature vulcanizing silicon rubber.
다양한 근사인수분해 알고리즘을 이용하여 압축성 유동장의 수렴성 및 유용성에 대한 연구
권창오,송동주 한국전산유체공학회 1999 한국전산유체공학회 학술대회논문집 Vol.1999 No.-
Convergence characteristics and efficiency of three implicit approximate factorization schemes(ADI, DDADl and MAF) are examined using 2-Dimensional compressible upwind Navier-Stokes code. Second-order CSCM(Conservative Supra Characteristic Method) upwind flux difference splitting method with Fromm scheme is used for the right-hand side residual evaluation. while generally first-order upwind differencing is used for the implicit operator on the left-hand side. Convergence studies are performed using an example of the flow past a NACAOO 12 airfoil at steady transonic flow condition, i. e. Mach number 0.8 at 1.25 0 angle of attack. The results were compared with other computational results in order to validate the current numerical analysis. The results from the implicit AF algorithms were compared well in low surface with the other computational results; however, not well in upper surface. It might be due to lack of the grid around the shock position. Because the algorithm minimizes the errors of the approximate decomposition, the improved convergence rate with MAF were observed.
비용매 유도 상변환 공정에 의한 Silicone Rubber-Polyetherimide 복합막 제조 및 VOC 제거에 관한 연구
권창오 김천대학교 2005 김천대학교 논문집 Vol.26 No.-
In the work, silicone rubber(SR) dense membrane was made from room temperature vulcanizing silicone rubber.
권창오,송동주,강신형 대한기계학회 1994 대한기계학회논문집 Vol.18 No.3
In this paper the CSCM type upwind flux difference splitting Navier-Stokes method has been applied to study the ARL-SL19 supersonic/transonic compressor cascade flow. H-type grid was chosen for its simplicity in applying cyclic tridiagonal matrix algorithm along with conventional slip/no-slip boundary conditions. The thin-layer algebraic model of Baldwin-Lomax was employed for the calculation of turbulent flows. The test case inlet Mach No. was 1.612 and inlet/exit pressure ratio($P_2/P_1$) was 2.15. The results were compared with experimental results from current method were compared well in suction surface with the experiments and other computational results; however, not well in pressure surface. It might be due to the complex flowfields such as shock/boundary layer interaction, turbulence, and flow separation, etc. In the future, a proper turbulence modelling and adaptive grid system will be studied to improve the solution quality.
졸-겔법에 의한 Li2O-Al2O3-SiO2-ZrO2,ZrO2 다공성 세라믹스의 제조
권창오 김천대학교 1993 김천대학교 논문집 Vol.14 No.-
Glasses of compositions LiO. A1,0, 4510, 0.03P,O, 0.09ZrO, were prepared by the sol-gel technique from metal alkoxides solutions and thermal treated to make a porous glass-ceramics. The results are as follows: 1. The gellation time was shortened as increase in the amonnt of added water. The optimum added water to production of a glass-ceramic was about three times as much as stoichiometric amount. 2. The specific surface area of the dried gel at 180°C was 280.4m2/8. And, the specific surface area of 154.64m2/g and 85. 14m2/g corresponded to 500°C and 700C, respe-ctively. They appeared to be in linear relationship and the mean pore radius distrib-ution of sintered gel was in the range of 7nm and 12nm. 3. The crystal of b-quartz solid solution was confirmed as heattreated at 750C, and the crystal of 8-eucryptite and b-quartz solid solution were detected in the sample at the heating temperature above 800°C
Upwind Navier-Stokes 방정식을 이용한 무딘 물체 주위의 유동장 해석
권창오,김상덕,송동주 한국전산유체공학회 1995 한국전산유체공학회 학술대회논문집 Vol.1995 No.-
In this paper the upwind flux difference splitting Navier-Stokes method has been applied to study the perfect gas and the equilibrium chemically reacting hypersonic flow over an axisymmetric sphere-cone(5˚) geometry. The effective gamma(r), enthalpy to internal energy ratio was used to couple chemistry with the fluid mechanics for equilibrium chemically reacting air. The test case condition was at altitude(30Km) and Mach number(15). The equilibrium shock thickness over the blunt body region was much thinner than that of perfect gas shock. The pressure difference between perfect gas and equilibrium gas was about 3 - 5 percent. The skin friction coefficient and heat transfer coefficient were also calculated.