航空科学技术
航空科學技術
항공과학기술
AERONAUTICAL SCIENCE AND TECHNOLOGY
2015年
2期
14-18
,共5页
联结翼%几何外形%气动布局%涡格法%气动特性%升阻特性
聯結翼%幾何外形%氣動佈跼%渦格法%氣動特性%升阻特性
련결익%궤하외형%기동포국%와격법%기동특성%승조특성
joined wing%geometric configuration%aeroadynamic configuration%vortex lattice method%aerodynamic characteristics%life-characteristic
联结翼飞机具有重量轻、刚度大、诱导阻力低等优势。采用涡格法，研究联结翼主要布局参数（前翼后掠角、前后翼展向连接点位置、前后翼垂直方向高度差）的变化对升力系数、阻力系数和最大升阻比的影响。所得计算结果对联结翼飞机气动布局参数的确定具有参考价值。
聯結翼飛機具有重量輕、剛度大、誘導阻力低等優勢。採用渦格法，研究聯結翼主要佈跼參數（前翼後掠角、前後翼展嚮連接點位置、前後翼垂直方嚮高度差）的變化對升力繫數、阻力繫數和最大升阻比的影響。所得計算結果對聯結翼飛機氣動佈跼參數的確定具有參攷價值。
련결익비궤구유중량경、강도대、유도조력저등우세。채용와격법，연구련결익주요포국삼수（전익후략각、전후익전향련접점위치、전후익수직방향고도차）적변화대승력계수、조력계수화최대승조비적영향。소득계산결과대련결익비궤기동포국삼수적학정구유삼고개치。
Advantages claimed for the joined wing aircraft include: light weight, high stiffness, low induced drag, and so on. This paper adopted the vortex lattice method to research and compare the impact of some geometric parameter changes which include the sweep angle of the front wing, the joined location of the front wing and the rear wing, the height difference of the front wing and rear wing on lift coefifcient, drag coefifcient and the maximum lift-to-drag ratio. The results obtained can be used as a guidance for the aerodynamic parameters design of the joined wing aircraft.
