摘要
在1.2m量级亚跨超声速风洞对某型飞机机头模型进行了DPIV高速选型实验,通过实验获得了两个机头模型的流场特性。实验结果表明:在巡航马赫数条件下,机头顶端速度分布平滑,不存在流动分离和超声速区;在快速巡航马赫数条件下,机头顶端存在局部很小区域的超声速区,强度很小,不存在流动分离。实验数据符合气动规律,实验数据可以作为机头气动设计的依据。
In the 1.2m trisonie wind tunnel of CAAA, the DPIV experiment of high-speed type selection of a certain designed aircraft nose was completed. Through the experiment, the flow field characteristics of two aircraft nose models were obtained. When on cruising flight, the flow field of aircraft nose is smooth, and flow separation and supersonic domain don＇t emerge. During fast cruising flight, local supersonic domain of low intensity emerges on the top of aircraft nose without flow separation. The experiment data accord with the aerodynamic law and can be regarded as the aerodynamic design foundation.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2012年第6期30-34,共5页
Journal of Experiments in Fluid Mechanics
关键词
飞机机头
DPIV
高速选型
风洞实验
aircraft nose
DPIV
high-speed type selection
wind tunnel test
