摘要
对后掠角分别为ｘ＝６０°、７０°和８０°尖前缘平板三角翼模型和一个前缘后掠角为（７６°＋４０°）的双三角翼模型在低速风洞中作大攻角俯仰谐波运动，振幅α＿ｍ＝３０°、６０°和９０°，缩减频率Ｋ＝０．０１～０．１２，基于根弦长雷诺数Ｒ＿ｅ＝２．７６×ｌ０￣５～８．２８×１０￣５。进行了六分量动态气动载荷测量，动态流动显示和７０°三角翼上翼面非定常压力测量，并分别与对应的静态试验结果比较。分析了运动参数包括缩减频率、振幅和Ｒ＿ｅ数、后掠角对气流动态迟滞特性的影响。
A large amplitude pitching cosine motion for x=60°, 70°and 80°sweep sharp leading-edge flat delta wings and a straked wing(76°+40°)with root chord of 400 mm was performed in a low-speedwind-tunnel.SiX-component dynamic airloads measurement, dynamic flowvisualization and unsteady surface pressure measurement on 70°deLtawing were conducted in the test conditions of amplitude α_m=30°, 60°and90°,reduced frequency K=0.01～0.12,Reynolds number R_e=2.76 ×l0￣5～8.28 × l0￣5 based wing root chord.The dynamic test results were com-pared with corresponding static results respectively.The effects of themotion parameters, such as amplitude,reduced frequency and R_e, sweepangle on aerodynamic behavior were given and discussed.
出处
《空气动力学学报》
CSCD
北大核心
1994年第4期367-374,共8页
Acta Aerodynamica Sinica
关键词
三角翼
大攻角
风洞试验
飞机
空气动力学
delta wing,high angle of attack, low speed aerodynamiccharacteristic,wind tunnel test.
