旋转弹箭气动导数与气动热仿真计算

摘要

Based on the shear stress transport ( SST) k-ω turbulent model, M910 bullet and F4 spinning missiles ' aerodynamic characteristics were simulated numerically in different attack of angle and different Mach number. Drag, normal force, pitching damping, rolling damping moment and Magnus moment coefficients were calculated by the method which combines CFD code and empirical formula. The results were compared with the experimental data and the error is mainly within the error of engineering. These results verifies the accuracy of the simulation method. Meanwhile, the results of these missiles' temperature contours and the temperature distribution of the center line of missiles' windward side in the condition of different spinning speed and different angle of attack were calculated. The results provide valuable reference for spinning missile's aero-thermo-elastic simulation.%研究弹箭气动特性优化问题，基于剪切应力传输( SST) k-ω湍流模型，分别对M910弹丸和旋转弹模型F4进行数值仿真。计算采用CFD和工程经验公式相结合的方法，得到了光弹M910和翼身组合体F4在不同攻角，不同旋转速度，不同马赫数下的气动导数分布。通过与实验数据比较分析，阻力系数，法向力系数，俯仰力矩系数导数，滚转阻尼系数误差均在工程误差范围内，验证了本文计算方法的准确性。同时，数值仿真得到旋转弹体绝热壁面温度分布云图和不同旋转速度、不同攻角的弹箭迎风面中心线上温度分布数据图。计算分析为旋转弹箭气动热弹性仿真提供有价值参考。