小型倾转旋翼气动特性试验研究
首发时间:2020-05-14
摘要:以8038旋翼为试验对象,开展了悬停、前飞和倾转过渡状态下旋翼气动特性试验研究,利用台架和风洞试验平台测量不同飞行模式下旋翼的气动性能。试验结果表明:悬停状态,旋翼气动力系数随着旋翼转速的增加而增大。前飞状态,随着前进比的增加,旋翼拉力系数降低,前方来流大小变化对旋翼气动力影响不大。倾转过渡状态,当旋翼倾角处于75 时,旋翼拉力系数随着入流比的增加而增大;当旋翼倾角小于60 ,旋翼拉力系数随着入流比的增加而减小。本文研究可为倾转旋翼飞行器设计提供气动数据。
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Experimental Study for the Aerodynamic Performance of a Small Tilt Rotor
Abstract:Ground tests are carried out to study the aerodynamic performances of Model 8038 rotor in hover, level flight and tilt transition state. The aerodynamic performance of the rotor including thrust and torque is measured using the test bench as well as the wind-tunnel. The experimental results show that the aerodynamic coefficient of rotor increases with the increases of rotation speed in hover state. The thrust coefficient decreases with the increases of advance ratio in level flight. And the variation of the flow speed has little effect on the aerodynamic load of the rotor. In transition state, the thrust coefficient increases with the increases of inflow ratio at tilt angle 75 ; the thrust coefficient decreases with the increases of inflow ratio as the tilt Experimental Study for the Aerodynamic Performance of a Small Tilt Rotorangle less than 60 . This paper can provide aerodynamic data for the design of tilt-rotor aircrafts.
Keywords: tilt rotor ground tests thrust coefficient advance ratio aerodynamic performance
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