小展弦比飞翼标模FL-2风洞跨声速开孔壁干扰特性修正研究

发布时间：2018-05-08 04:04

  本文选题：壁压 + 洞壁干扰　； 参考：《空气动力学学报》2016年01期

【摘要】：为了满足现代风洞试验精细化要求,提高风洞试验数据精准度,开展跨声速开孔壁洞壁干扰修正方法研究。本文利用实测壁压信息构造开孔壁边界条件,通过求解N-S方程,模拟试验模型在风洞中的绕流场,建立基于壁压信息的跨声速洞壁干扰非线性修正方法。不同于线性修正方法,本方法可用于各种复杂外形飞行器的亚、跨声速开孔壁洞壁干扰修正,结合小展弦比飞翼标模风洞试验数据,对其在FL-2风洞试验数据开展洞壁干扰特性研究。洞壁干扰修正结果表明,洞壁干扰量随马赫数变化呈增长趋势,Ma=1.0左右达最大,经过修正的FL-2风洞的跨声速试验结果,与FL-26风洞近似无干扰试验结果吻合良好。
[Abstract]:In order to meet the requirements of modern wind tunnel test and improve the accuracy of wind tunnel test data, the transonic wall interference correction method was studied. In this paper, the boundary conditions of the open hole wall are constructed by using the measured wall pressure information. By solving the N-S equation and simulating the flow field around the wind tunnel, a nonlinear correction method of transonic wall interference based on the wall pressure information is established. Different from the linear correction method, this method can be used for the subsonic and transonic wall interference correction of aircraft with complex shapes, and combined with the wind tunnel test data of small aspect ratio flying wing. The wall interference characteristics of FL-2 wind tunnel test data are studied. The results of wall interference correction show that the volume of wall interference increases with Mach number to the maximum. The modified FL-2 wind tunnel transonic velocity test results are in good agreement with the FL-26 wind tunnel approximate non-interference test results.
【作者单位】： 中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室;
【分类号】：V211.74
，

本文编号：1859860