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采用自主开发的数值软件SPACER对典型气动布局在Ma=6.0(Re=1×107)高超声速巡航时的气动力性能进行了数值评估。评估的气动布局包括类乘波体(仿X-51A)、翼身融合体(仿ISR)、传统升力体(仿X-33)和轴对称锥形体(仿Fasthawk导弹)。由于升力体范围较广,还对一种相对扁平的升力体模型进行了数值评估。评估结果表明:在考察条件下,类乘波体具有较大的升阻比和较小的阻力,是很有潜力的高超声速巡航气动布局;翼身融合体和传统升力体需一定的改进和进一步的研究,如扁平升力体的气动性能可得到大幅提升;轴对称锥形体以其总阻力小,也具有一定优势。
The aerodynamic performance of a typical aerodynamic layout at hypersonic maneuver of Ma = 6.0 (Re = 1 × 107) was evaluated by a self-developed numerical software SPACER. The aerodynamic layout evaluated includes Class X-51A, Wing-Like Fusion (ISR), Conventional Lifting Body (X-33) and Axisymmetric Cone (Faux Fasthawk). Due to the wide range of lift bodies, a relatively flat lift body model was also evaluated. The results of the assessment show that under the conditions of investigation, the class-based multiplication wave body has a large lift-drag ratio and a small resistance, which is a promising hypersonic cruising aerodynamic layout. The wing-body fusion body and the traditional lift body need some improvement and Further research, such as the flat lift body aerodynamic performance can be greatly enhanced; axial symmetric cone with its total resistance is small, but also has some advantages.