Abstract
A rectangular symmetrical wing model is studied in a low-speed wind tunnel to examine the effects of wind shear by measuring lift, drag, and pitching moment. The model is subjected to a uniform flow normal to the free stream, and a three-component balance system attached to a computer allowed measurement of the three moments. The uniform flow impinging on the model simulates the wind shear, and the effect of the shear is found to cause a significant reduction in lift and a similarly significant increase in drag. Increases in the wind-shear velocity are found to increase the stall angle of attack and therefore the maximum lift coefficient. It is concluded from the results of the investigation that when a microburst is encountered both thrust and angle of attack should be boosted to counteract the effects. (C.C.S.)