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介绍了装有后退式微型后缘装置(Rearward Mini-TED)的NACA23012翼型在低雷诺数条件下的表面压力分布、气动力和PIV速度场的风洞实验结果,并与NACA23012原型翼的对应测量结果进行了对比分析,以探讨Mini-TED装置对翼型流场、气动特性产生的影响。本实验风速为15m/s,以弦长为特征量的雷诺数为Re≈1.3×105,翼型表面压力分布采用测压孔和压力传感器测量,通过积分获得翼型升力和压差阻力,并利用尾耙测量翼型受到的总阻力。结果表明,后退式Mini-TED翼型改变了翼型周围的流场速度分布和尾流流动结构,导致上翼面吸力和下翼面的压力升高,使翼型升力增加,但压差阻力也增加。同时发现后退式Mini-TED翼型使前驻点位置后移,加快了上翼面的流动速度,后缘分离受到抑制。
The surface pressure distribution, aerodynamic forces and PIV velocities of NACA23012 airfoil with rearward Mini-TED under low Reynolds number are introduced, and the results of the wind tunnel experiment are compared with that of NACA23012 prototype wing The results of the measurements were compared and analyzed to investigate the effect of the Mini-TED on the airfoil flow field and aerodynamic characteristics. The experimental wind speed is 15m / s, and the Reynolds number characteristic of the chord length is Re≈1.3 × 105. The airfoil surface pressure distribution is measured by the pressure-measuring hole and the pressure sensor, and the airfoil lifting force and the pressure drop resistance are obtained through integration Tail rake is used to measure total resistance of airfoil. The results show that the retractable Mini-TED airfoil changes the velocity distribution and the wake flow structure around the airfoil, resulting in the increase of suction pressure on the upper airfoil and the pressure on the lower airfoil, Also increase. At the same time, it is found that the retreating Mini-TED airfoil moves the position of the former stagnation point forward and accelerates the flow velocity of the upper airfoil. The trailing edge separation is suppressed.