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정성기(S. K. Jung),명노신(R. S. Myong),조태환(T. H. Cho),박경린(G. R. Park),강태우(T. W. Kang) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.11
Ice accretion on aircraft surface can greatly deteriorate the aerodynamic performance of aircraft. Especially, air flows around a wing at glaze ice conditions are very complex and can suffer large aerodynamic penalties. Complicated horn shapes are usually found on the surfaces at glaze ice conditions by coupling effects of heat flux and shear stress. Therefore, the conventional structured CFD method has difficulty in the prediction of glaze ice shape due to its limitation on handling complex geometry. For example, negative cell volumes can be generated in the structured grids in the process of grid regeneration. In order to overcome this limitation, unstructured CFD method was employed to calculate an Eulerian-based droplet field and ice accretion on the surfaces. The developed codes were then compared with experimental data. It was shown that the collective efficiency and iced shape were in good agreement with previous results.
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.
등속도로 하강중인 회전 낙하산의 공력특성에 관한 수치적 연구
제상언(S.E. Je),정성기(S.G. Jung),곽상혁(S.H. Kwag),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2006 한국전산유체공학회지 Vol.11 No.1
In this paper a method for analysing aerodynamic characteristics of a rotating parachute in steady descending motion is presented Because of a complex geometric configuration of the parachute associated with side vents and discontinuous skirts, special procedure was adopted to handle the geometry in the analysis. A panel method was successfully applied to the present problem and yielded good results using above procedure. A CFD code using the full Navier-Stokes equations was also applied and produced good results. Parachute free drop and wind tunnel tests were performed to determine the fully developed canopy configuration and aerodynamic characteristics. The method can be used for optimizing the parachute size and side vent configurations.
정기영(K.Y. Jung),안국빈(G.B. Ahn),정성기(S.K. Jung),명노신(R.S. Myong),조태환(T.H. Cho),신훈범(H.B. Shin),정주현(J.H. Jung),최영호(Y.H. Choi),김정훈(J.H. Kim) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
Ice accretion on aircraft surface can greatly deteriorate the safety of aircraft. In particular, it can be a cause of impediment for aircraft performances such as aerodynamic characteristics, control, and engine. Numerical simulation of icing accretion based on the state-of-art CFD techniques can be alternative to expensive icing wind tunnel test or flight test. In this study, icing conditions are defined in order to predict the ice accretions around the air intake of aircraft. Then the range and amount of ice accretion on the intake in icing wind tunnel were investigated. In addition, a study on the size effect of icing wind tunnel was conducted in order to check the compatibility with the real in-flight test environment.
박경린(G.R. Park),양영록(Y.R. Yang),정성기(S.K. Jung),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
An integrated multi-disciplinary design system plays a critical role in the preliminary design of an aircraft. In this paper such system is developed for the multi-disciplinary computation and design; aerodynamics, elasticity, and radio frequency stealth. Common data base of geometry and structured grids is generated and used for aerodynamic, structural and electromagnetics analysis. The Navieri-Stokes CFD, FEM, and CEM technique are used for aerodynamic, structural, and RF stealth computations, respectively.
정기영(K.Y. Jung),안국빈(G.B. Ahn),명노신(R.S. Myong),조태환(T.H. Cho),정성기(S.K. Jung),신훈범(H.B. Shin) 한국전산유체공학회 2012 한국전산유체공학회지 Vol.17 No.2
Ice accretion on the surface of aircraft in flight can adversely affect the safety of aircraft. In particular, it can cause degradation of critical aircraft performances such as maximum lift coefficient and total pressure recovery factor in engine air intake. In this study, computational prediction of ice accretion around a rotorcraft air intake is conducted in order to identify the impingement region with high droplet collection efficiency. Then the amount of ice accretion on the air intake, which is essential in determining the required power of ice protection system, is calculated. Finally, the effect of icing wind tunnel size is investigated in order to check the compatibility with the real in-flight test environment.