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《JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS》 1997-03
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EFFECT OF OUTBOARD LEADING EDGE BLUNTNESS OF DOUBLE DELTA WINGS ON VORTEX FLOW CHARACTERISTICS

Feng Yanan\ \ Wu Cheng\ \ Xiong Shanwen (Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics)  
An experimental study is presented that has been caried out in a low speed wind tunnel on tow double delta wing models having leading edge sweep angles of 75°/45° and 75°/60°. The study has been conducted to investigate the effects of the wing leading edge shape on the vortex flow characteristics by using flowfield measurement. The test results indicate that the outboard leading edge of the double delta wing being blunted causes inboard vortex and outboard vortex close each other and stronger interaction and results in the merged vortex moving inward and downward at high angles of attack. The blunted outboard leading edge induces higher total pressure coefficient and axial velocity of the outboard vortex core or joined vortex core than that generated by the corresponding sharp leading edge wing, hence the bursting of the outboard vortex or joined vortex is delayed.
【Fund】: 航空科学基金
【CateGory Index】: O354.1
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