基于非定常CFD方法跨声速民用飞机标模俯仰气动导数计算研究  

Static and Dynamic Pitch Derivatives of Transonic Full Aircraft Configuration with Unsteady CFD Method

作　　者：朱海涛 白文 

机构地区：[1]中国航空研究院航空数值模拟技术研究与应用中心,北京100012

出　　处：《航空科学技术》2017年第7期19-24,共6页Aeronautical Science & Technology

摘　　要：采用非定常计算流体力学(CFD)方法和动网格技术,计算了跨声速民用飞机全机构型TCR气动标准模型在0°~30°迎角范围内气动力系数的时均值、俯仰静导数和俯仰动导数;通过与试验结果对比,研究了非定常CFD方法在较大迎角范围内对包含鸭翼、垂尾等部件的复杂外形气动导数的计算精度。与试验结果对比表明,在16°~24°迎角范围内,受鸭翼和机翼上流动分离再附以及内外翼分离涡相互作用等复杂流动结构的影响,俯仰力矩系数的动导数与试验数据有相对较大的差异。Time averaged aerodynamic force coefficients, static derivative and dynamic derivative for full aircraft configuration TCR model at attack angle of 0° -30° were computed through unsteady CFD method with moving mesh in order to investigate the capability of the method to complex geometries. Numerical results show that the time averaged value, static derivative and dynamic derivatives of both normal force coefficient and pitch moment coefficient basically agree with the experimental datum which verifies the accuracy of the method. As to the complex separation flow in the canard and wing at angle of attack 16°-24°, there are obviously differences between the numerical results and experimental datum for pitch moment coefficient.

关 键 词：动导数 静导数 非定常 动态气动力 全机构型 TCR模型 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]