低背鳍对细长平板三角翼大迎角空气动力的影响  

Effect of Low Dorsal Fin on Aerodynamic Characteristics of Slender Delta Wing

作　　者：孟宣市[1] 乔志德[1] 高超[1] 罗时钧[2] 刘锋[2] 

机构地区：[1]西北工业大学翼型叶栅国防科技重点实验室,陕西西安710072 [2]美国加州大学尔湾分校机械与宇航工程系,加利福尼亚926973975

出　　处：《航空学报》2007年第3期545-549,共5页Acta Aeronautica et Astronautica Sinica

基　　金：西北工业大学博士创新基金(CX200501)

摘　　要：对细长体平板三角翼和加上两个不同高度背鳍后的组合体在低速风洞进行了六分量天平测力实验，三角翼后掠角82．5°，背鳍当地高度与模型当地半展长比值分别为0．3和0．6，实验迎角范围12°～32°，包括1．66×10^6和2．33×10^6两个雷诺数。实验结果表明：0°侧滑角下，在翼面上发生旋涡破裂前，单独细长平板三角翼的横向力及横向力矩在实验迎角范围内始终为零；加上两个不同高度的低背鳍后，在一定的迎角下，三角翼的横向力及横向力矩开始不为零，流场定常；在更大的迎角下，流场变得非定常。实验结果初步验证了前人关于细长锥体分离涡的稳定性理论，并给出了旋涡失稳后，随着迎角的增大，流场进一步发展的状态。A force measurement experimental study was performed on a flat-plate delta wing of 82.5° sweep angle and combination of the identical delta wing with low dorsal fins. The test was conducted at the low-speed wind tunnel using a six-component internal strain-gage balance at 12°-32° angles of attack. Two fins of differ ent heights were tested, and the ratios of the local fin height to the local wing semi-span were 0.3 and 0.6 respectively. There were two Reynolds numbers, 1.66 × 10^6 and 2.33 × 10^6 ,used. The measurements of the aerodynamic forces and moments clearly indicate that no lateral force occurs over the wing alone model at 0° sideslip and lower angles, but a steady force-asymmetry occurs over the wing-fin model at certain angles, and the vortex flow becomes unsteady at higher angles of attack. The results prove for the first approach force measurement evidence of the validity of the vortex stability theory of Cai, Liu and Luo and depict the flow be havior after the onset of the vortex instability with increasing angle of attack.

关 键 词：涡的稳定性 大迎角 背鳍 细长体 平板三角翼 

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]