大展弦比飞机模型边界层转捩模拟技术  

Simulation of boundary layer transition on a high aspect ratio aircraft model

作　　者：周岭[1] 何彬华[1] 李建强[1] 刘奇[1] 宋书恒[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2013年第3期357-361,共5页Acta Aerodynamica Sinica

摘　　要：针对大展弦比飞机模型高速风洞试验需求,进行了边界层转捩模拟技术研究。研究表明:与传统的金刚砂粗糙带相比,柱状转捩带具有粘贴牢靠、可操作性强等优势,已经推广应用于大展弦比飞机模型高速风洞试验;边界层转捩对大展弦比飞机模型气动特性有重要影响,不仅影响阻力,而且对升力与俯仰力矩均有明显影响;在目前国内低雷诺数风洞条件下建议在边界层固定转捩条件下进行风洞试验,以提高风洞试验精度。Test techniques with boundary layer transition have been investigated to meet the high speed wind tunnel test requirements of aircraft models with high aspect ratio wings. Investigation results indicate that, compared with the grit-type carborundum, the cylindrical transition trips have an advantage of more re- peatable and controlled pattern, and thus are used in high speed wind tunnel tests of aircraft models with high aspect ratio wings. Not only drag characteristics, but also lift and pitching moment are all affected by boundary layer transition for aircraft with high aspect ratio wings. Thus, it is suggested that, in order to im- prove the test accuracy, testing in wind tunnels of low Reynolds numbers be conducted with fixed transition.

关 键 词：边界层转捩 大展弦比机翼 风洞试验 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]