In this research, low speed wind tunnel tests have been carried out to investigate the canard configuration and location on the pressure distribution over a maneuverable aircraft model. The applied wing and canard are delta shape with a sharp leading-edge. The investigations have been performed at free stream velocity of 18 m/sec, angles of attack of 14 and 18 degree, and different canard angles respect to the main wing. The main wing sweep angle is 60 degree and the canards have the sweep angles of 60 and 70 degrees with different thicknesses. The velocity distribution over the main wing was measured at three canard positions, including low, mid and up respect to the main wing, and the pressure distribution was measured only at mid and up canard positions. The results showed that the vortex which is generated over the wing having a sharp leading edge canard is stronger and bigger than the vortex of the delta wing having a rounded leading edge. Also, at the up position of the canard, maximum pressure reduction over the wing surface is observed. Furthermore, by increasing the wing sweep angle and decreasing the canard thickness, higher pressure reduction would be obtained.