分离形式后体喷流试验技术及阻力修正方法

Sleeve-type afterbody jet experiment technique and its drag correction method

详细介绍了分离形式后体喷流模型设计中需要注意的关键技术问题,以及相应的设计方法。针对某型飞机高速风洞后体喷流测力试验,以提高分离形式后体喷流试验中的阻力测量精度为目的,精细化设计后体喷流模型的密封以及内外腔压监测点,采用对风洞试验中天平阻力项结果进行修正的方法,得到与国外同类型试验阻力测量精度相一致的结果,阻力测量精度0.0005,证明该修正方法能有效地应用于分离形式后体喷流试验阻力数据的修正,精度满足国军标阻力测量指标。

In this paper, we introduced the design method for sleeve-type afterbody jet experiment and key aerodynamic characteristics in the design. In order to improve the accuracy of drag measurement for sleeve-type afterbody jet-effect test of a certain aircraft in a high-speed wind tunnel,a seal form and the positions of pressure measurement were elaborately designed at the nozzle annular clearance gap and cross section,respectively. A correction method was applied to the measured drag. The experiment results show that the accuracy of the measured drag is 0. 0005. This accuracy is consistent with that in similar jet experiment conducted in abroadtunnel. In addition,the present correction method used is effective for the drag correction in thesleeve-type jet experiment. The measuring accuracy meets the requirement of the GJB （China National Military Standard）.