三种跨声速洞壁干扰修正方法及其在小展弦比飞翼标模试验中的应用  

Three types of transonic wind tunnel wall interference correction method and their application on low aspect ratio flying wing calibration model

作　　者：钟世东[1] 李巍[1] 苏继川[1] 李永红[1] 贺中[1] 

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000

出　　处：《空气动力学学报》2016年第1期113-118,共6页Acta Aerodynamica Sinica

摘　　要：在FL-24风洞进行了带壁压信息测量的小展弦比飞翼标模测力试验,并在FL-26风洞进行了洞壁干扰验证试验。本文利用小扰动位流壁压信息法、全速势位流方法、基于RANS的壁压信息法三种方法开展飞翼标模的洞壁干扰修正研究,并与试验结果进行了比较。结果表明,飞翼标模洞壁干扰呈现与翼身尾常规布局不同的规律,三种方法在飞翼标模洞壁干扰修正中有各自的适用性。Force test on wall pressure measurement has been conducted in CARDC FL-24 wind tunnel,and the corresponding verification test has been carried out in CARDC FL-26 wind Tunnel for a flying wing calibration model with low aspect ratio.Three types of transonic wind tunnel wall interference correction method,i.e.,small perturbation wall pressure signature correction method,full potential equation method and RANS based wall pressure signature correction method,are adopted to calculate wall interference.The calculation results are compared with test result.It shows that the wall interference tendency of low aspect ratio flying wing calibration model is different from that of a wing-body-tail configuration.The three methods have their individual applicability when they are used for flying wing configuration wall interference correction.

关 键 词：飞翼标模 洞壁干扰 数值模拟 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]