한국전산유체공학회:학술대회논문집

Korean Society of Computational Fluids Engineering (한국전산유체공학회)
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PREDICTION OF THE AERODYNAMIC CHARACTERISTICS OF AN ORBITAL BLOCK OF A LAUNCH VEHICLE IN THE RAREFIED FLOW REGIME USING DSMC APPROACH

DSMC 해석기법을 이용한 희박유동 환경에서의 발사체 Orbital Block 공력특성 예측

  • 김영훈 (한국항공우주연구원 열/공력팀) ;
  • 옥호남 (한국항공우주연구원 열/공력팀) ;
  • 최영인 (한국항공우주연구원 열/공력팀) ;
  • 김인선 (한국항공우주연구원 열/공력팀)
  • Published : 2007.04.06
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Abstract

The aerodynamic coefficients of Apollo capsule are calculated using a DSMC solver, SMILE, and the results agree very well with the data predicted by NASA. The aerodynamic characteristics of an orbital block which operates at high altitudes in the free molecule regime are also predicted. For the nominal flow conditions, the predicted aerodynamic force is very small since the dynamic pressure is extremely low. And the additional aerodynamic coefficients for the analysis of the attitude control are presented as the angle of attack and the side slip angle vary from $+45^{\circ}\;to\;-45^{\circ}$ of the nominal angle.

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