动态试验中支架对三角翼涡破碎影响研究  

Effect of Support on Vortex Breakdown of Delta Wing in Dynamic Tests

作　　者：丁克文[1] 张庆利[1] 张文华 

机构地区：[1]南京航空航天大学动力工程系,南京210016

出　　处：《南京航空航天大学学报》1999年第5期534-538,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：航空科学基金;国家自然科学基金

摘　　要：在南京航空航天大学低速风洞中用前缘后掠角分别为６５°和７０°三角翼模型，采用不同厚度和不同位置安装的类似后横向支架进行过失速非定常破碎涡的测定实验，涡及破碎点位置由ＴｉＣｌ４ 烟流显示，并用相机记录。实验表明，在非定常过失速情况下，涡的破碎位置与非定常气动力一样具有迟滞环特性。在同样攻角条件下，随着类似后横向支架的加高，或其位置越靠近三角翼模型后缘，无论静态、上仰、下俯，涡破碎点位置均更靠近三角翼模型前缘。The location of vortex breakdown point for 65° and 70° swept delta wing models oscillating in a pitch to high angles of attack is measured in low speed wind tunnel in Nanjing University of Aeronautics and Astronautics.The dummy crosswise support of different heights is fixed at different places during model tests.The location of vortex and vortex breakdown point is shown by smoke flow and is recorded with a camera. Results of the test show that the location of vortex breakdown point in unsteady experiments,like unsteady aerodynamic loads, would produce hysteresis loops.The location of vortex breakdown point,at the same constant angle of attack,moves continuously forward to the leading edge of the delta wing as the dummy support grows in height, or is nearer to the dummy support back edge of the delta wing,whether static, pitchup or pitchdown.

关 键 词：动态试验 支架 三角翼 涡破碎 风洞试验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.41