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IR 신호 분석을 위한 비행 조건에 따른 노즐 열유동장 해석
전수환(S.H. Chun),양영록(Y.R. Yang),문혁(H. Moon),김준영(J.Y. Kim),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
Plume flow-fields of aircraft nozzles are numerically investigated at various flight conditions for infrared signature analysis. A mission profile of subsonic unmanned combat aerial vehicle is considered for the requirement of each mission, associated engine and nozzles are selected through a performance analysis. Numerical results of nozzle plume flow-fields using a CFD code are analyzed in terms of thrust, maximum temperature. It is shown that maximum temperature increase for lower altitude and higher Mach number.
항공기 IR 신호 분석을 위한 다양한 비행 조건에서의 노즐 열유동장 해석
전수환(S.H. Chun),양영록(Y.R. Yang),문혁(H. Moon),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2011 한국전산유체공학회지 Vol.16 No.3
Aerothermodynamic flowfields of aircraft engine nozzles are computatkmally investigated at various flight conditions for infrared signature analysis. A mission profile of subsonic unmanned combat aerial vehicle is considered for the case study and associated engine and nozzles are selected through a performance analysis. Computational results of nozzle and plume flowfields using a density-based CFD code are analyzed in terms of thrust, maximum temperature, length and optical thickness of plume. It is shown that maximum tempera lure, length, and optical thickness of nozzle plume increase for lower altitude and higher Mach number.
정성기(S.K. Jung),오진근(J.G. Oh),전수환(S.H. Chun),문혁(H. Moon),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
Ice accretion on aircraft surface can greatly impair the aerodynamic performance of aircraft. As an alternative to the traditional Lagrangian particle tracking approach, an Eulerian-based droplet impingement and ice accretion code for air flows containing water droplets was developed. A CFD solver was also developed to solve the clean airflow. The results of present method were compared with experimental data and previous icing codes such as LEWICE and FENSAP-ICE and were confirmed to show good agreement each other in qualitative and quantitative ways.
아음속 무인 항공기 IR 신호 저감을 위한 다양한 노즐 형상에 따른 열유동장 특성 전산 예측
김준영(J.Y. Kim),전수환(S.H. Chun),서은호(E.H. Seo),장민욱(M.W. Jang),명노신(R.S. Myong) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.5
Aerothermodynamic flowfield characteristics of nozzles were computationally investigated at various nozzle configuration in order to reduce infrared signature. A virtual UAV nozzle was designed through mission and performance analysis. Nozzle and plume flowfield at maximum power was analyzed using a density-based CFD code. Finally, qualitative information for the infrared signature reduction design was obtained through the analysis of the flowfield characteristics at various nozzle configuration.
강은지(E.J. Kang),문혁(H. Moon),전수환(S.H. Chun),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.11
Aerodynamic coefficients of a re-entry vehicle are numerically investigated at various Mach numbers using a CFD cod. An adaptive grid method is utilized in order to enhance the accuracy of computational simulation. The force and moment coefficients are compared with available experimental data. It was found that the aerodynamic coefficients for various Mach numbers are in close agreement with the data.
전산 공력해석을 통한 재진입 비행체의 조종성 및 안정성 연구
강은지(E.J. Kang),김준영(J.Y Kim),전수환(S.H. Chun),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.5
In this study, the stability and controllability of a re-entry vehicle were computationally investigated. Various Mach numbers, angles of attack, and control surface deflection angles were considered. Aerothermodynamic analysis based on a CFD code, FLUENT, was conducted in nominal TAEM condition (Mach 3?11). In all cases, normal force coefficients decreased along with increasing of control surface deflection angle, while axial force coefficients increased along with increasing of angle of attack. Also, the derivative of pitching moment coefficient was found negative, indicating the static stability in these flight conditions.