三维桨尖旋翼桨叶表面压力测量试验
Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics（2011）
Abstract
研制了三维桨尖(抛物线后掠下反桨尖)4 m直径模型旋翼,并在旋翼试验台和大型低速风洞中完成了该模型旋翼的气动特性试验.采用了新的桨叶表面压力传感器布埋技术,有效地开展了三维桨尖旋翼桨叶表面非定常压力测量风洞试验.试验结果表明,下反桨尖的压力系数随方位角变化幅值比非下反桨尖的小,桨尖下反可以减弱桨-涡干扰,且随前进比增大,压力系数的峰值也增大.
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Key words
Helicopter,Pressure measure,Rotor,Three-dimensional blade tip
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