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윤성환(S.H. Yoon),김종암(Chongam Kim),허기훈(K.H. Hur) 한국전산유체공학회 2010 한국전산유체공학회 학술대회논문집 Vol.2010 No.5
In this study, NASA test model with four cruciform fins is utilized to validate the in-house code. Surface pressure distribution and aerodynamic coefficients are compared with experimental data. Through extensive validation work, it is verified that the code has capability to predict aerodynamic characteristics of missile configuration. In inviscid analysis through a relatively low computational time, analysis result close to experimental data can be confirmed. However, at high angle of attack more than 20 degree, the accuracy of analysis is gradually decreased due to massive separation. In addition, it has been seen that Reynolds number, turbulence model and numerical method have effects on body vortices and aerodynamic characteristics.
고범용(B.Y. GO),백연식(Y.S. Baik),이은석(E.S. Lee),이재은(J.E. Lee),허기훈(K.H. Hur) 한국전산유체공학회 2013 한국전산유체공학회 학술대회논문집 Vol.2013 No.5
A control fin is necessary for the flying object in order to satisfy its stability and maneuverability. In general, a tail is selected as a control fin and the control effectiveness of the tail is very important. Therefore, it is required to study the variables which have influence on tail performance. When side jets are located ahead of tails, the flow field around tails has interferences with side jets. So the aerodynamic characteristics of a missile with side jet is different from that of a missile without side jet. In this study, the influences of side jet on the missile aerodynamics are investigated by use of the computational fluid dynamics. The aerodynamic characteristics are found be affected by not only the free stream conditions, e.g. free stream velocity, angle of attack and bank angle but also the jet conditions, e.g. the temperature and gas property of jet.