超临界翼型射流环量控制的数值计算

为提高飞行器的升力特性,改善起飞着陆和机动性能,研究了射流环量控制对超临界翼型气动特性的影响。基于计算流体力学,对影响计算效率和精度的网格参数进行了优化设计,得到一种高效高精度网格的剖分方法;并以此为基础,建立超临界翼型环量控制的计算模型,求解雷诺平均N-S方程,分析了环量控制在不同动量系数和迎角下的作用效果,数值计算结果与实验结果基本一致。结果表明:环量控制大大提高了翼型的气动特性,且在小迎角或负迎角就可以产生较大的升力,但是动量系数并不是越大越好。计算结果可为进一步研究环量控制对飞行器的影响奠定理论基础。

Numerical Calculation of Circulation Control by Blowing on Supercritical Airfoil

In order to improve the takeoff and landing performance of the modern aircraft and motor performance ,this paper studies the effect of circulation control on characteristic of lift-to-drag .Through the research methods of computational fluid dynamics ,the grid parameters are optimized designed ,which can affect the calculations′accuracy and efficiency ,the grid subdivision method of high precision and efficiency is obtained.On this basis,calculation model of supercritical circulation control airfoil is set up ,solve Renault average N-S equation ,at different angles of attack and the momentum coefficient ,effects of circulation control are analyzed , the calculation results are consistent with the experimental results .Results show that a larger lift can be obtained at a lower or negative angle of attack ,but the greater the momentum coefficient is not ,the better characteristics of lift are .The calculation results can be used as theoretical basis of further research work of effect of circulation control on aircraft .