Abstract: The main purpose of test study is to find out the effect of drag reduction technique by hybrid laminar flow control Using NACA0006 series laminar airfoil as physical model, using FLUENT CFD software to calculate and analyse pressure grads of airfoil surface. Uniting optimi-zation local figure of airfoil surface to enlarge positive pressure grads region and disposal leading edge suction control unit of airfoil to come into being drag reduction technique by hybrid laminar flow control. Testing laminar flow area with infrared image in low speed wind tunnel contrasting using drag reduction technique by hybrid laminar flow control and without it. The analysis of the results give the conclusion: the laminar flow area of airfoil surface become larger in evidence after using drag reduction technique by hybrid laminar flow control. The results satisfy the goal of the research.