An extensive experimental study has been performed to investigate the wind tunnel sidewall effect and the boundary layer suction on a half model pressure distribution. A three-dimensional half wing was made according to its full span model. The wing was tested at angles of attack ranging from ?= -5 to 25 degree and at Reynolds numbers of 0.5*106, 1.0*106 and 1.3*106 in a subsonic wind tunnel. Experimental results such as static pressure distribution, lift coefficient, and wake are compared with the corresponding 2-D results from that of similar model. Wind tunnel sidewall boundary layer suction effects on the surface static pressure distribution has been studied at various conditions has been studied. The results show that the flow over the portion of the model effected by the sidewall pressure separates at an angle of attack which is smaller than the corresponding angle for other portion of the wing. This phenomenon yields an increase in the drag coefficient and a noticeable decrease in the value of the lift coefficient. However, when suction was applied to the sidewall, separation was delayed to higher angles, and the corresponding aerodynamic loads varied significantly.
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