A NUMERICAL STUDY OF FLOWFIELD AT A SUPERSONIC INLET BY CHANGING ANGLES OF ATTACK AND CHANNEL LENGTH

초음속 흡입구의 통로길이와 받음각에 따른 유동장 변화 연구

The flow characteristics on a supersonic inlet with bleeding system by changing angles of attack and channel length conditions are studied by computational 3D turbulent flow analysis. A compressible upwind flux difference splitting Navier-Stokes method with $k-{\omega}$ turbulence model is used to analysis the inlet flowfield. More non-uniform flowfields are shown at the AIP when angle of attack becomes bigger and bigger. These non-uniform flowfield works the performance aggravating factors of the supersonic engine. Non-uniform flowfield by changing channel length at the various angle of attack are investigated.