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采用风洞实验的方法,在不停风且固定迎角和几何构型的情况下,通过对比有、无人为脉动压力扰动时多段翼型升力特性的变化,证明多段翼型缝道流动的脉动参数(包括脉动速度和脉动压力)对其升力特性有着不可忽视的影响。人为扰动源为模型表面埋设的有源式蜂鸣器。蜂鸣器出口20mm处的声压级约为60dB。实验表明,在研究范围内,弱声学扰动可使翼型的升力系数降低。升力系数的减少量随扰动的位置、频率变化而变化,最大减少量为1.8%。提出在多段翼型的实验评估工作中需要注意风洞本底噪声、模型尺度、加工质量对缝道脉动压力和脉动速度等参数的影响以及相应升力特性的变化。
Wind tunnel experiment is used to demonstrate the fluctuating flow in multi-section airfoil slides by comparing the lift characteristics of multi-section airfoils with or without pulsating pressure disturbance under the condition of steady wind and constant angle of attack and geometry. Parameters (including pulsation velocity and pulsation pressure) have a significant impact on the lift characteristics. Artificial disturbance source is the active buzzer buried on the surface of the model. The sound pressure level at 20mm at the exit of the buzzer is about 60dB. Experiments show that in the research area, the weak acoustic disturbance can reduce the lift coefficient of the airfoil. The reduction of lift coefficient varies with the position and frequency of the disturbance, with a maximum reduction of 1.8%. It is suggested that the influence of wind tunnel noise, model scale, processing quality on parameters such as the fluctuating pressure and pulsation velocity, and the corresponding lift characteristics should be paid attention to in the experimental evaluation of multi-section airfoils.