刘岩松 杜宇凡 高婷

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，该方程能直观方便得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。为验证模拟方法的準确性，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。

关键词：CFD仿真平面拘束运动网格划分三维建模

中图分类号：V221+.3 文献标识码：A

Aerodynamic Coefficient Calculation Method of Aircraft Based on CFD Numerical Simulation

LIU Yansong  DU Yufan  GAO Ting

（Shenyang Aerospace University， Shenyang， Liaoning Province， 110136 China）

Abstract：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.

KeyWords： CFD simulation;Planar constrained motion;Meshing;3D modeling

飞机动力学建模是基于气动、动力、结构、总体等提供的飞行器数据库，构建飞机动力学模型，探寻其飞行力学规律，并指导制导控制系统设计。准确高效的获得气动力系数是开展飞行器动态特性研究与设计方案改进的重要前提。目前获取气动力系数的方法有风洞试验、经验公式估算、CFD仿真。风洞实验是一种模拟实验，具有效率高、成本低、实验条件可控的优点[1]。在真实飞行时，静止大气是无边界的。而在风洞中，气流是有边界的，边界的存在限制了边界附近的流线弯曲，会对模型流场的产生干扰[2]。经验公式估算获取气动力系数的方法存在着数据处理繁琐、计算周期长、效率低等主要问题。随着计算机技术的发展，具有成本低、速度快、资料完备且可模拟各种不同的工况等独特的优点的CFD仿真技术得到了广泛应用。……