支板阻力特性实验  

Experimental investigation on drag of strut

作　　者：苏义[1] 刘卫东[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2009年第12期2643-2648,共6页Journal of Aerospace Power

摘　　要：实验在超燃冲压发动机直连式试验台进行,燃烧式加热器出口气流马赫数为2.7,总温为1 337 K.利用推力测量系统对不同结构尺寸支板的冷流阻力和热试阻力进行了研究.比较了高度分别为37.5 mm和71 mm,后掠角分别为0°,30°和45°的支板冷流阻力,结果表明支板的冷流阻力随支板高度的增大而增大,随后掠角的增大而减小;实验还在燃烧模态下对不同当量比时支板的阻力进行了对比,结果表明支板的热试阻力比冷流阻力小,且支板的热试阻力随当量比的增加而减小.Experiments were conducted in a scramjet direct-connected wind tunnel facility with a combustion heater,which supplies Mach 2.7 airflow with a total temperature of 1 337 K.The drags of struts with different heights(H=37.5,71 mm) and sweepback angles(0°,30°,45°) were studied by a thrust-measuring system.Experimental results in cold flow indicate that,the drag of strut rises with increase of height and declines with increase of sweepback angles.The drags of struts under combustion condition of different fuel ...

关 键 词：超燃冲压发动机 支板 阻力 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]