Abstract:

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.

Key words: wall interfenence, wind tunnel tests, airfoil