一种宽速域乘波三角翼气动布局设计  

Wide-speed aerodynamic layout adopting waverider-delta wing

作　　者：陈树生 张兆康 李金平 冯聪 高正红[1] CHEN Shusheng;ZHANG Zhaokang;LI Jinping;FENG Cong;GAO Zhenghong(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Lab of Aerospace Power System and Plasma Technology,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]空军工程大学航空动力系统与等离子体技术全国重点实验室,西安710038

出　　处：《航空学报》2023年第23期229-244,共16页Acta Aeronautica et Astronautica Sinica

基　　金：中国科协青年人才托举工程(2022QNRC001)。

摘　　要：针对宽速域高超声速飞行器亚/跨/超/高超声速气动性能难以兼顾的问题,发展出一种融合乘波前体和大后掠三角翼的宽速域高超声速气动布局。乘波前体设计基于锥导乘波理论,设计马赫数为Ma=5;小展弦比大后掠机翼采用基于代理模型优化设计的宽速域翼型。数值模拟结果表明:亚声速状态下,该布局能够在大迎角飞行时利用涡升力改善气动性能,升阻比可以维持在8以上;超声速下该宽速域气动布局的三角翼双“S”构型下表面使气动布局尾缘附近获得额外加载,高超声速下乘波体前缘的激波特性提升了气动布局的升阻性能,超/高超声速速域内升阻比不低于4.5,巡航性能良好。此外,对该宽速域乘波三角翼气动布局的纵向静稳定性进行了分析,该气动布局整体气动中心位置靠后。To overcome the difficulty in inclusive consideration of the subsonic/transonic/supersonic/hypersonic aerodynamic performance of hypersonic vehicles in wide-speed range,we propose a wide-speed-range hypersonic aerodynamic configuration with a waverider forebody and a large swept delta wing.The design of the waverider forebody is based on the conical flow theory.The design Mach number is 5.The wide-speed range airfoil based on the surrogate model optimization design is arranged on a large swept wing with a small aspect ratio.The result shows that in subsonic flight,the configuration can improve aerodynamic performance using vortex lift at high angles of attack,with the lift-drag ratio maintained above 8.In supersonic flight,the double “S” shaped lower surface of the delta wing enables additional loading near the trailing edge of the aerodynamic configuration.In hypersonic flight,the shock wave characteristics at the leading edge of the waverider improve the lift-drag performance.The lift-drag ratio in the supersonic/hypersonic speed range is no smaller than 4.5 with good cruise performance.In addition,the longitudinal static stability in the wide-speed range is analyzed,showing that the aerodynamic center of the aerodynamic configuration is near the tailing edge.

关 键 词：宽速域 高超声速 乘波体 三角翼 涡升力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]