摘要
为探讨鸭式布局飞机全机流场随迎角的演变规律 ,分别对无鸭翼布局与鸭式布局两种情况于北航大水洞进行了染色液流场显示实验。同时 ,为与水洞结果对比分析 ,给出了风洞测力部分结果。鸭式布局模型除鸭翼以外 ,包括机身、基本翼、翼前小边条及垂尾和腹鳍 ,其中鸭翼相对机身负偏 1 0°。显示结果表明 ,对两种布局而言 ,涡系结构都非常复杂。无鸭翼布局的机身涡很强 ,且机身涡对边条涡、翼根涡有明显诱导作用 ,三涡相互绕合并向展向偏折。鸭式布局的机身涡由于鸭翼存在其强度变弱 ,边条涡与翼根涡绕合趋势增强 ,两涡最终合并为单一集中涡并向外翼偏折 ,且其涡核位置较无鸭翼布局更靠近机翼前缘。鸭式布局主翼涡破裂较无鸭翼布局有所延迟 ,但鸭翼自身涡系破裂较早。
To explore the flow field development with angle of attack on the canard configuration aircraft,a water tunnel flow visualization investigation was performed on both canard on and canard off configuration aircraft models in BUAA.At the same time,the lift results of wind tunnel were given to compare with the water tunnel results.Canard on model,except canard,included fuselage,primary wings,small strakes before the primary wings,twin fins and ventral fins.The canard deflected 10° negatively.The flow visualization indicated,for both configurations,that vortex system was very complicated.For canard off configuration,the fuselage vortex was very strong,and strake vortex and wing root vortex were induced evidently by it.The three vortices twisted each other and deflected along wing span direction.For canard on configuration,the intensity of the fuselage vortex became weak because the canard existed,but strake vortex and wing root vortex twisted more evidently,and they formed single concentrated vortex at last.The concentrated vortex deflected along wing span di rection and the vortex core was nearer to the wing leading edge than that of canard off configuration. The wing vortex breakdown on canard on configuration was delayed relative to that on canard off configuration,but the canard vortex broke down very early.
出处
《流体力学实验与测量》
CSCD
北大核心
2002年第3期26-31,共6页
Experiments and Measurements in Fluid Mechanics
关键词
鸭式布局
流场显示
飞机
涡干扰
canard configuration
flow visualization
vortex interference
