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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 3-D blade tip (parabolic swept down counter-tip) 4 m diameter model rotor was developed. The aerodynamic performance of the model rotor was tested in a rotor test rig and a large low speed wind tunnel. A new blade surface pressure sensor embedding technique was adopted to effectively carry out the wind tunnel test on the unsteady pressure measurement of three-dimensional blade tip rotor blades. The experimental results show that the pressure coefficient of lower tip tip changes with the azimuth angle smaller than that of the non-lower tip, and the tip of the tip can weaken the propeller-vortex interference. As the forward ratio increases, the peak value of pressure coefficient increases Big.