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中文摘要：
采用自主开发的数值软件SPACER对典型气动布局在Ma=6．0（Re：1×10^7）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。
英文摘要：
The aerodynamics of typical aircraft configurations under Ma= 6.0 （Re=-1 × 10^7） cruise condi- tion was evaluated numerically using in-house software SPACER. The configurations include quasi-waverider （like X-51A）, blended-wing-body （ISR）, traditional lifting-body （X-33） and axisymmetric cone （Fast- hawk）. A flat lifting-body model was also studied in this paper. It is found that, at the current conditions, the quasi-waverider has good lift-to-drag ratio and relatively small drag force, which is the most potential hy- personic configuration among studied; the blended-wing-body and lifting-body require modifications to im- prove the performance, such as to flat the shape of the lifting-body; the axisymmetric cone is also a candidate for hypersonic cruise configuration due to the small drag.
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