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三维桨尖旋翼桨叶表面压力测量试验 被引量：8

Measurement of Blade Pressure Distribution for Three-Dimensional Blade Tip
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摘要 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。 A model rotor with sweptback parabolic anhedral tip is designed and tested both in rotor test rig and low speed wind-tunnel.The rotor blade pressure is surveyed by a new laying technology for pressure sensors.As a result,the extent of rotor blade pressure for anhedral tip is lower than that of non-anhedral tip and grows higher with the increase of forward velocity.The new type anhedral tip also may weaken the blade vortex intercation（BVI） on a certain extent.
作者 林永峰 刘平安 陈文轩 陈雪松 黄水林
机构地区 中国直升机设计研究所直升机旋翼动力学重点实验室
出处 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2011年第3期346-350,共5页 Journal of Nanjing University of Aeronautics & Astronautics
关键词 直升机 旋翼 三维桨尖 压力测量 helicopter rotor three-dimensional blade tip pressure measure
分类号 V211.52 [航空宇航科学与技术—航空宇航推进理论与工程]
  • 相关文献

参考文献11

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二级参考文献25

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共引文献13

同被引文献63

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  • 2张莉,吕明.基于特征分解的一步最小二乘声源定位算法[J].电声技术,2007,31(5):42-45. 被引量：4
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引证文献8

二级引证文献14

南京航空航天大学学报
2011年 第3期

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