摘要
Erisson对高升力多段翼型的洞壁干扰问题进行过理论计算。Moury和Labrujère对上述问题也进行过一些研究,可惜Moury的实验是在开闭比为20％的开孔壁风洞中进行的,而Labrujère仅给出个别情况的实验结果,且其测压点较多,计算较繁。
Due to the fact that the influence function possesses a character of focusing itself (i.e., there are some regions on the wall where the influence function and the tunnol-width/model-span ratio are independent), the number of the necessary circumferential pressure measurement stations can be dropped into a few, when the wall pressure correction method is employed for computing the three-dimensional wall interference. By adopting two-section or three-section method, the influence of the longitudinal displacement can also be eliminated. The present paper extends the aforementional measure to the wind tunnel interference correction for two-dimensional, high-lift, multicomponent airfoil testings.The advantages of the present method are renderred from the reduction of measurement stations, simplifying the data processing, and its capability of performing real time data processing.The models of GA(W)-1, LS(l)-041 ?Mod and NACA2415 are investigated in NH-2 wind tunnel. The corrected results obtained by the present method agree well with other correction methods.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第6期B324-B329,共6页
Acta Aeronautica et Astronautica Sinica
关键词
洞壁干扰
风洞实验
翼型
高升力
wall interfenence, wind tunnel tests, airfoil.
