摘要
针对高超声速通气模型内阻测量存在的误差大的问题,首次采用DPIV技术和总压测量排架相结合的方法测量了超燃发动机尾喷管流场速度矢量和皮托压力分布,间接获得了内流出口处平均马赫数和静压平均值,从而实现了高超声速通气模型内阻测量。研究结果表明:DPIV试验获得的粒子图像可以清楚地显示喷管出口位置内外流的分界面、内外流混合层的尾迹、通气模型外表面边界层;DPIV试验获得的速度矢量场结果准确、精度高,能够提供远远超出传统测量技术所能提供的流场信息。DPIV技术作为一种有力的测量手段,在高超声速飞行器研究中能够发挥重大的作用。
Because the scramjet after-body nozzle is asymmetric, it is difficult to test outlet flow of hypersonic flowthrough model, and there exists large error during internal drag measurement. In this paper, DPIV(Digital Particle Image Velocimetry) and total pressure rake are combined together to measure velocity vector field and pitot pressure field of outlet flow of scramjet for the first time, thus the mean Mach number and mean static pressure can be computed indirectly, and internal drag measurement of hypersonic flowthrough model can be achieved. Results obtained show that particle images of DPIV can clearly display the interface between internal and external flow and the wakes of boundary layer. DPIV technique can supply accurate velocity vector fields which possess much more information than measurement results of traditional test techniques. As a powerful test tool, DPIV can play an important role in the research of hypersonic air vehicle.
出处
《应用力学学报》
CAS
CSCD
北大核心
2014年第2期182-187,306,共6页
Chinese Journal of Applied Mechanics
关键词
通气模型
高超声速飞行器
内阻测量
DPIV,flowthrough model,hypersonic vehicle,internal drag measurement.
