摘要
利用无限插值法生成结构化动网格,耦合求解欧拉方程与结构方程,分别模拟了二维带操纵面翼型以及三维NASP机翼周围跨音速流动。对二维带操纵面翼型嗡鸣发生时的流场进行了分析,发现操纵面上的激波后会产生巨大的分离区,且分离区的变化过程滞后于激波变化过程,认为缝隙的存在对嗡鸣发生有促进作用;对三维NASP机翼的研究发现操纵面质量比的增加可以延缓嗡鸣发展。
The flow field around two- dimensions airfoil with control surface and three- dimensions NASP wing was simulated. The deforming structured grid was generated by TFI method. Euler equations were solved coupled with structural equations. By studying the flow field of two- dimensions airfoil when control -surface occurring, it was found that there was a large separated region behind the shock wave on the control- surface and the evolvement of the region was lag behind that of the shock wave. It was inferred the gap could accelerate the control- surface buzz. By studying the NASP wing, it was found the evolvement of control- surface buzz could be deferred by enlarging the specific mass.
出处
《航空计算技术》
2012年第3期77-80,共4页
Aeronautical Computing Technique
