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为实现飞行器外形根据来流条件变化做出相应调整,需深入了解变形体非定常气动现象和机理。以典型超临界翼型为研究对象,分别制定了翼型厚度及弯度变形方案,实现了翼型柔性变形。利用数值仿真方法在高雷诺数条件下开展了翼型厚度、弯度连续变形带来的非定常效应。结果表明,翼型厚度、弯度连续变形均会形成明显的升、阻力系数迟滞环,且频率越高、幅度越大,变形导致的非定常效应也越强;相对而言,翼型弯度变形产生的非定常效应较厚度变形产生的非定常效应更明显。最后通过分析流线图及压力系数分布图发现,流动结构随几何变形的迟滞性会导致非定常效应的产生。
In order to adjust the shape of the aircraft according to the changes of the conditions of the incoming flow, the unsteady aerodynamic phenomena and mechanism of the deformable body need to be further understood. Taking the typical supercritical airfoil as the research object, the scheme of airfoil thickness and camber deformation was developed respectively, and the flexible deformation of airfoil was realized. The unsteady effects of continuous deformation of airfoil thickness and camber are carried out under high Reynolds number conditions by using numerical simulation method. The results show that the continuous deformation of the airfoil and the camber will result in obvious hysteresis loop of rising and drag coefficient. The higher the frequency and the larger the amplitude, the stronger the unsteady effect caused by the deformation. Relatively speaking, the deformation of the airfoil camber The unsteady effects of thicker deformations have more pronounced unsteady effects. Finally, by analyzing the flow chart and the pressure coefficient distribution chart, it is found that the hysteresis of the flow structure with the geometric deformation leads to the generation of the unsteady effect.