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신훈범(H.B. Shin),최원(W. Choi),서석주(S.J. Seo),유진복(J.B. Ryu) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
Ice accretion is one of the potential hazards in airplane flight, adversely affecting aircraft aerodynamic. There are two distinct icing analysis that can be simulated. One is predicting the effect of ice on the aerodynamic performance of airfoils when ice geometry is known. The other is simulating ice accretion. This work presents the method of icing accretion analysis. This work presents an Eulerian approach to calculate the droplet collection efficiency on the 2D airfoil. The initial flow solution are obtained the FLUENT and copled with droplet motion in the ambient condition.
신훈범(H.B. Shin),김지홍(J.H. Kim),정훈화(H.H. Jung) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.11
This study presents the analysis process for prediction of anti/de-icing systems. In previous studies, Icing analysis code based on Fluent(Commercial code) has been developed to simulate the droplet trajectory, ice shape and temperature distribution on the heated surface. In this study, It shows the results which contain the validation with several tests.
항공기 엔진베어 내 소화장치 성능예측을 위한 전산해석방법 연구
신훈범(H.B. Shin),서석주(S.S. Joo),정주현,유진복 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
There is fire dangers inside engine bay where fuel of oil leakge can be ignited by hot engine surfaces. So, Fire suppressor is needed to extinguish the flames. The current FAA requirement is that the concentration level should be greater than 6% by volume throughtout the protected zone for longer than a half second simultaneously. To Satisfy the FAA requirement, The Fire extinguish system should quickly delivery the fire extinguish agents and Fire extinguish system should be designed effectively. This study is to develop and simulate the injection of fire extinguish agents into the engine-bay. Transient simulations were performed and predicted the concentration of fire extinguish agents at the certain locatioin in the engine-bay.
신훈범(H.B. Shin),유진복(J.B. Ryu) 한국전산유체공학회 2012 한국전산유체공학회 학술대회논문집 Vol.2012 No.5
This study presents the process of icing analysis to predict the icing shapes and performance of anti/de-icing systems. To predict the particle trajectory and collection efficiency on the 2D airfoil, The trajectory code is developed using the UDS(User Defined Scalar Transport Framework) of FLUENT. Energy balances are performed to predict the surface temperature distribution on the 2D airfoil. A various tests results which contain the ice shapes and temperature distribution are considered to validate the numerical method and results.
신훈범(H.B. Shin),유진복(J.B. Ryu) 한국전산유체공학회 2011 한국전산유체공학회 학술대회논문집 Vol.2011 No.5
The hot gas reingestion phenomenon of helicopter brings about the reduction of engine power available around in-ground. The phenomenon will vary for the conditions of ambient conditions and engine exhaust gas, the flow field associated with the downwash effect of main rotor. To verify the amount of hot gas reingestion to intake, Tests(Wind tunnel test, Flight test) or CFD could be available. At this study, the reingestion around in-ground would be predicted by numerical anaslysis(CFD).
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.
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.