基于CFD数值仿真的飞行器气动系数计算方法  

Aerodynamic Coefficient Calculation Method of Aircraft Based on CFD Numerical Simulation

作　　者：刘岩松[1] 杜宇凡 高婷 LIU Yansong;DU Yufan;GAO Ting(Shenyang Aerospace University,Shenyang,Liaoning Province,110136 China)

机构地区：[1]沈阳航空航天大学,辽宁沈阳110136

出　　处：《科技创新导报》2021年第27期9-11,共3页Science and Technology Innovation Herald

摘　　要：为便捷地求取飞行器的气动力系数,本文以Bryan所提出的刚性对称飞行器运动方程为理论基础,该方程能直观方便地求出所需的力及力矩。通过仿真得到各方向速度分量后,拟合系数,构建气动力模型方程。在小扰动状态时,根据纵向及横侧向运动状态下得出的气动力系数构建方程,所得出的结果与CFD仿真模拟结果接近。为验证模拟方法的准确性,将所求得的数据与风洞试验数据进行比对,其误差符合要求,说明在设计初期运用该方法求得设计机体的气动力系数是可行的。In order to obtain the aerodynamic coefficients of the aircraft conveniently,this paper takes the rigid symmetrical aircraft motion equation proposed by Bryan as the theoretical basis.The equation can intuitively and conveniently obtain the required force and moment.After the velocity components in each direction are obtained by simulation,the fitting coefficient is used to construct the aerodynamic model equation.In the small disturbance state,the equations are constructed based on the aerodynamic coefficients obtained in the longitudinal and lateral motion states,and the obtained results are close to the CFD simulation results.In order to verify the accuracy of the simulation method,the obtained data is compared with the wind tunnel test data,and the error meets the requirements.It shows that it is feasible to use this method to obtain the aerodynamic coefficient of the designed engine block in the early stage of design.

关 键 词：CFD 仿真 平面拘束运动 网格划分 三维建模 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]