基于改进涡格法的飞翼布局飞机稳定性导数计算  

Predicting Stability Derivatives of Flying Wing Aircraft Based on Improved Vortex Lattice Method

作　　者：宋磊[1] 杨华[1] 解静峰[1] 黄俊[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《南京航空航天大学学报》2014年第3期457-462,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：由于没有垂直安定面,无尾飞翼布局飞机航向安定性通常接近中立或略微为负,造成了其横航向稳定性与常规布局飞机具有很大区别。因此无尾飞翼布局飞机在概念设计阶段,必须在进行气动性能优化的同时,计算获得较为准确的气动导数数据以对飞机横航向稳定性进行分析,这对气动计算软件计算精度和效率提出了很高的要求。本文在现有涡格法计算软件的基础上,提出了改进算法。以一概念飞翼布局飞机为算例进行计算,结果与风洞实验结果的对比证明:飞机具有侧滑角的情况下,改进算法比原算法计算精度有明显提高。Because the absence of vertical stabilizer causes neutral or slightly negative yaw stiffness, the flying wing aircraft differs from conventional configuration aircraft in lateral directional stability. Thus in the conceptual design stage of tailless aircraft, not only aerodynamic characteristics need to be opti- mized, but also the relatively accurate stability derivatives are necessary to analyze the dynamic stability of aircraft. It requires higher accuracy and efficiency of aerodynamic calculation program. An improved vortex lattice algorithm is proposed in this paper. A certain tailless aircraft is chosen to be tested in wind tunnel and calculated with the improved algorithm. The comparison of the results shows that the improved algorithm has made progress in accuracy during sideslip.

关 键 词：涡格法 稳定性 无尾飞翼布局 飞行器 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]