摘要
利用三个几何相似的 RAE104翼型模型,用实验方法确定西工大翼型风洞(TAWX)的无堵塞干扰开闭比。对于不带测压轨及带测压轨两种状态的开槽壁分别采用2%及4%开闭比可认为近似于无堵塞干扰。利用测压轨测量该翼型风洞上下壁附近控制面的静压分布,并利用快速富里叶变换法计算马赫数及迎角修正量。由 TAWX 风洞与西德 DFVLR TWB 风洞实验结果的比较可以看出,当迎角为零时,两者结果吻合较好,说明无堵塞干扰开闭比的确定基本上是正确的,经过快速富里叶变换法进行马赫数及迎角修正后的 TAWX 有升力的实验结果也与 TWB 结果接近。
The open-area-ratio of the Transonic Airfoil Wind Tun-nel Xian(TAWX)determined by experiments using 3 geometrical sim-ilar models is 4% or 2% corresponding to testing with or without pres-sure rails,and can be considered to be free from blockage effect.Pressure rails are used to measure the pressures of the control sur-faces near the top and bottom walls.The Math number and angle ofattack corrections are calculated by using Fast Fourier Transform(FFT)method.The agreement of the experimental results between TAWX and TWB(Transonic Airfoil Wind Tunnel Braunschweig,West Germany)is usu-ally satisfactory at zero angle of attack.The TAWX test results afterbeing corrected using FFT method are close to those of TWB.
关键词
跨音速流
翼型
风洞
洞壁干扰
transonic flow
airfoil wind tunnel
wall interference corrections
