三角翼过失速非定常洞壁干扰修正

分别以固壁条件和洞壁附近实测的压力分布，模拟各类实壁和透气壁试验段的洞壁边界条件，利用N-S方程数值求解模型在风洞中的绕流场，得出洞壁干扰对跨音速模型绕流的影响和气动力修正结果。初步研究结果表明，该方法能较有效地模拟模型在跨音速风洞中的绕流场，GBM04A模型在0.6m风洞中的试验结果经洞壁干扰修正后与无干扰参考结果吻合较好

UNSTEADY WALL CORRECTIONS FOR A DELTA WING OSCILLATING IN PITCH TO VERY HIGH ANGLES OF ATTACK

Unsteady tunnel wall corrections for a delta wing oscillating in pitch to very high angles of attack were presented, applying influence functions in steady wall pressure correction method and unsteady wall pressure at the optimum points. Results of this study showed that the unsteady wall corrections, just like unsteady aerodynamic load, produce hysteresis loops, The unsteady wall correction values were increasing with the reduced frequencies increase at the begining, and then afterward on the contrary. For the same ratio of wing span to test section width, the unsteady wall correction values for a delta wing with a sweptback angle of 70° were greater than those with a sweptback angle of 60°.