旋翼模型桨叶表面压力测量试验  

The Blade Surface Pressure Measurement Test of Rotor Model

作　　者：兰波[1] 武杰[1] 黄明其[1] 

机构地区：[1]中国空气动力研究与发展中心低速所,绵阳621000

出　　处：《直升机技术》2008年第3期125-128,共4页Helicopter Technique

摘　　要：采用"桨叶表面预先压槽,再粘贴片式压力传感器并粘胶带再开测量孔"的方法测量旋翼模型桨叶表面压力,在8m×6m风洞完成了地面悬停和风洞前飞试验,研究了桨叶表面压力测量技术和数据采集处理技术,获得了桨叶表面特征剖面的压力分布,建立了实用的旋翼模型桨叶表面压力测量试验技术。The hover test and wind tunnel forward flight test of pressure measurement rotor models was conducted using the method of squeezing the blade surface to form slots,then pasting the ultarminiature thin pressure transducers and covers sensors with paster.This article researched the technique of blade surface pressure measurement,data acquiring and processing,and obtained the pressure distributions of blade typical sections,and constructed an applied technique of the blade surface pressure measurement of rotor model.

关 键 词：旋翼模型 试验台 动态压力测量 风洞试验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]