双尾撑布局飞机气动特性计算分析  

Aerodynamic performance computations and analysis of a twin-boom configuration airplane

作　　者：王晓璐 吴登宇[1,2] 苗楠 刘战合 WANG Xiaolu;WU Dengyu;MIAO Nan;LIU Zhanhe(School of Aeronautical Engineering,ZUA,Zhengzhou 450046,China;Institute of Unmanned Aerial Vehicle,ZUA,Zhengzhou 450046,China)

机构地区：[1]郑州航空工业管理学院航空工程学院,河南郑州450046 [2]郑州航空工业管理学院无人机研究院,河南郑州450046

出　　处：《飞行力学》2020年第4期7-10,21,共5页Flight Dynamics

基　　金：航空科学基金资助(2016ZA55001);河南省科技攻关计划资助(202102210267);河南省高等学校青年骨干教师培养计划资助(2019GGJS181);河南省高层次人才国际化培养计划资助(2020-19)。

摘　　要：为研究双尾撑布局飞机气动性能,提出了常规布局和双尾撑两种布局方案,并进行了计算和分析对比。对计算模型进行了网格收敛性分析,计算了两种布局巡航速度时迎角在-9°~18°范围内的气动特性,并对比分析了两种布局升阻特性和俯仰力矩特性。结果表明,两种布局的升阻比变化趋势一致,在最大升阻比附近,双尾撑布局的升阻比略大于常规布局;在俯仰力矩系数的线性变化区间,双尾撑布局斜率较常规布局高29.8%。就本文算例而言,双尾撑布局的失速改出特性优于常规布局。A twin-boom configuration,along with a classic configuration were presented to investigate the aerodynamic performance of the former one based on computations and analysis.Grid convergence analysis was conducted before comparisons.Aerodynamic characteristics including lift,drag and pitching moment for both configurations were presented for cruise speed and wide range of angles of attack(-9°~18°).The tendencies of lift-to-drag ratio are almost the same,while the twin-boom configuration is better near the maximum value.The slope of pitching moment curve in the linear range for twin-boom configuration is 29.8%larger than the classic one.The twin-boom configuration shows better spin recovery ability than the conventional one.

关 键 词：双尾撑布局 通用航空飞机 气动特性 数值模拟 

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]