后缘修型对空腔流场特性影响分析  

Analysis of the effect of the modification at the trailing edge on cavity flow characteristics

作　　者：吴继飞[1] 陶洋[1] 范召林[1] 罗新福[1] 

机构地区：[1]中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000

出　　处：《空气动力学学报》2010年第2期197-202,共6页Acta Aerodynamica Sinica

摘　　要：本文以风洞试验为手段,在高速风洞中对空腔流场特性进行了较为深入的研究,通过对空腔底部静态压力以及脉动压力的测量,分析后缘修型对腔底流场特性的影响。研究结果表明,后缘修型对空腔流场特性影响随修型半径增大而增强;当空腔流场类型为开式穴流动、过渡式穴流动和闭式穴流动,后缘修型对腔内静态压力分布的影响不大,而当空腔流场为过渡—开式穴流动时,后缘修型可能使空腔的流场类型发生转变并使静态压力梯度明显增大;研究结果还表明,后缘修型能有效降低腔内的噪声强度,但对空腔能量尖峰的抑制效果会因试验条件的改变而产生差异。An experimental investigation was conducted in a high speed wind tunnel to explore cavity flow characteristics. Detailed static-pressure and fluctuating pressure measurements were obtained at the cavity floor to enable the effect of the modification at the trailing edge to be determined. Results indicate that the modification has no obvious effect on static pressure distributions if the cavity flow type is the open flow, transitional flow or closed flow. Bot the cavity flow type may be changed and the cavity static pressure gradient may be increased remarkably by the modification if the cavity flow type is transitional/open flow. The study also indicates that the modification can reduce the intensity of noise markedly, but its effect on cavity tones depending on test conditions.

关 键 词：空腔 流场类型 压力梯度 空腔能量尖峰 

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]