摘要
为设计一种新型宽速域滑翔飞行器,基于无粘锥导乘波设计理论,设计了Ma=4和Ma=8状态下的乘波构型,并将其进行"串联"拼接,得到一类新型宽速域乘波飞行器。采用数值模拟方法对此类飞行器的气动特性进行了研究,得到其流场特征和气动特性。结果表明,采用新型"串联"高超声速乘波飞行器,其气动性能在宽速域范围内比单马赫数条件下的乘波飞行器气动性能更优。"串联"乘波体的升阻比随马赫数的增加而变大,当Ma>8时,其气动特性变化不明显,最大升阻比接近3.2,在设计马赫数范围内,升阻比不低于2.6。升阻比随攻角的增加先变大后减小,在3°攻角时升阻比最大。在Ma=6时,基准模型-1的最大升阻比为4.714,"串联"乘波体的升阻比达到3.48。
In order to design a novel hypersonic cruise vehicle for a wide-ranged Mach numbers,two different configurations in two situations（Ma=4 and Ma=8）based on the theory of waverider were designed,and then combined to achieve a novel hypersonic vehicle for a wide-ranged velocity.In this study,the commercial software Fluent was employed to numerically investigate its aerodynamic performance and flow field characteristics.The obtained results show that the aerodynamic performance of the novel combined waverider vehicle is better than that of single Mach number waverider vehicle for the wide-ranged velocity.With the increasing of Mach numbers,the lift-to-drag ratio of the novel waverider increases continually,but the gradient decreases.Its maximum value is nearly 3.2,and the value is not lower than 2.6 in the range of design Mach number.The lift-to-drag ratio first increases,and then decreases with the increasing of the angle of attack.When the angle of attack is 3°,the lift-to-drag ratio is the largest.When the Mach number is 6,the maximum value of the benchmark-1 is 4.714,and the value of the combined waverider reaches 3.48.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第5期588-592,共5页
Journal of Solid Rocket Technology
基金
国家自然科学基金(90816027)
国防科技大学校预研基金(JC11-01-02)
中国航天科技集团公司航天科技创新基金
航空科学基金(20110188003)
关键词
宽速域飞行器
气动性能
升阻比
乘波体
wide-ranged vehicle
aerodynamic performance
lift-to-drag ratio
waverider
