Numerical Simulation of Supersonic Inlet Flow

초음속 흡입구 유동의 수치모사

  • 곽인근 (인하대학교 일반대학원 항공우주공학과) ;
  • 유일용 (인하대학교 일반대학원 항공우주공학과) ;
  • 이승수 (인하대학교 기계공학부 항공우주공학) ;
  • 정석영 (국방과학연구소)
  • Published : 2009.05.14


Numerical simulations of flows in an axisymmetric supersonic inlet with bleed regions were performed. For the simulations, the existing code which solves the RANS(Reynolds Averaged Navier-Stokes) equations and 2-equation turbulence model equations was transformed to axisymmetric form and bleed boundary condition was applied to the code. In this paper, the modified code was validated by comparing the results against an experimental data and other computational results for flow on a bump and over an oblique shock with bleed region. Using the code, numerical simulations were performed for the flow in the inlet with multiple bleed regions.