论文部分内容阅读
利用定常壁压洞壁干扰修正法算出的影响函数和洞壁最佳点测出的非定常壁压数值，进行低速风洞三角翼过失速非定常洞壁干扰修正。研究表明，非定常洞壁干扰修正有类似非定常空气动力的所谓滞迟环现象。非定常洞壁干扰修正量随频率增大开始增大，以后随频率增大而减小，呈现所谓“风洞谐振”趋势。在同样模型展长与风洞宽度之比条件下，前缘后掠７０°三角翼洞壁干扰修正量大于前缘后掠６０°三角翼
Based on the influence function of the correction method of steady wall pressure wall interference and the value of unsteady wall pressure measured at the optimum point of the wall, the unsteady wall disturbance correction of low speed wind tunnel delta wing over stalling is carried out. Studies have shown that the correction of unsteady tunnel walls has a so-called hysteresis loop similar to unsteady aerodynamics. The correction of unsteady wall interference increases with the increase of frequency and then decreases with the increase of frequency, presenting the so-called “wind tunnel resonance” trend. Under the condition of the same model length and the width of the wind tunnel, the interference correction amount of the front edge swept 70 ° delta wing cavity wall is greater than that of the front edge swept 60 ° delta wing