中文摘要：

参考公开文献资料,建立了一个气动外形类似于美国X-51A的飞行器模型,采用Fluent软件对其进行了数值模拟,得到了飞行器在迎角-10°～10°范围和马赫数6条件下内外流场结果及升力系数、阻力系数和升阻比等气动特性,并与国内参考模型及国外公开文献的结果进行了对比,评估了这种气动外形的可用性及迎角变化对其内外流场和基本气动特性的影响。

英文摘要：

A num which was figured out erical investigation on aerodynamic characteristics of an X-51A-like aircraft model, based some published literatures, was carried out at angles of attack from-10°to ＋10° and flight Mach number 6. The basic aerodynamic characteristics such as the lift coefficient, drag coefficient and lift/drag ratio etc. were obtained and examined with available experimental data from public literatures. The applicability of the model as well as the influence of angle of attack upon aerodynamic flow field and per- formance was evaluated.