In order to study low speed aerodynamic characteristics of the high speed forward swept wing (FSW) aircraft,taking a combined model of the FSW with NACA64A005 high speed thin airfoil and the fuselage as the bas-ic research object,and adding the corresponding backward swept wing (BSW) model and strake FSW model, the longitudinal aerodynamic experiments of the models were carried in a low speed wind tunnel.The test angle of at-tack is -4° to +36°, wind speed 29 m/s, characteristic Reynolds number 4×105.The results show that the low speed lift-drag characteristics of the FSW is basically the same as the BSW under the test condition, but the FSW shows good aerodynamic performance developing trend in the high angle of attack.The lift characteristics and aero-dynamic efficiency of the FSW with the slender strake is improved obviously, where the area of the strake is only 5.2% of the wing area.Compared with the basic FSW, the maximum lift coefficient of the strake FSW is increased about 40% at the angle of attack 33°.Based on the FSW model and wind tunnel test condition,the aerodynamic numerical simulation of the steady and viscous 3D flow field is carried by ICEM and FLUENT software and RANS equations.The results show the modeling and boundary condition setting are reasonable, and the simulation can support analysis of the wind tunnel model test data.%为了研究高速前掠翼飞机低速气动力变化特性,以一种NACA64A005高速薄翼型前掠翼翼身组合体模型为基本研究对象,包括相应后掠翼模型和细长边条前掠翼模型,开展模型纵向气动力低速风洞实验研究,模型攻角变化范围-4°～+36°,实验风速29 m/s,特征雷诺数4×105.结果表明:前掠翼模型与相应后掠翼模型升力和阻力变化特性基本相同;但前掠翼表现出较好的大迎角气动力性能发展趋势.翼根前加装面积仅为机翼面积5.2%的大后掠细长边条后,前掠翼模型升力特性和气动效率明显提升,33°迎角最大升力系数比基本前掠翼提高约40% .依据模型风洞实验实际条件,采用ICEM和FLUENT软件与雷诺时均N-S方程,进行前掠翼模型定常黏性空间流场气动力数值仿真,结果表明建模和边界条件设置合理,仿真计算能够支持分析风洞模型实验数据.
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