3D Numerical Simulation of Clamshell Thrust Reverser with Flap Deployed while Landing
The flow field distribution characteristic of a clamshell thrust reverser with flap deployed while landing is investigated based on Computational Fluid Dynamics (CFD) technology. The mesh was generated with unstructured tetrahedron and unstructured hexahedron meshes and S-A turbulent model in solving Reynolds averaged N-S equations is adopted. The results show, in the range of landing speed between 136.1m/s and 17.0m/s, the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet; and it impinges on part of the aerofoil and pylon. As landing speed decreases, the hot reverse exhaust flow spreads forward and laterally deeper, so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough, which will result in inlet distortion. When landing speed decreases down to 34m/s, the hot reverse exhaust flow starts to impinge on the ground, which may wind up some dross to the inlet. At last, the reverse thrust decreases as landing speed decreases.
clamshell thrust reverser:flap:hot reverse exhaust flow:inlet distortion:reverse thrust
LIU Chunyang WANG Zhanxue WANG Jiaqi YIN Fang KONG Deying
School of Power and Energy,Northwestern Polytechnical University,Xian 710072,China. The First Aircraft Institute of AVIC,Xian 710089,China
国际会议
哈尔滨
英文
156-160
2010-01-08（万方平台首次上网日期，不代表论文的发表时间）