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 cor-rection method,full potential equation method and RANS based wall pressure signature correc-tion 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 indi-vidual applicability when they are used for flying wing configuration wall interference correction.
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