An experimental study on airfoils with spoilers is performed. The study was carried out by testing of a two dimensional model in the Military Technical College low speed wind tunnel. At Reynolds numbers of approximately 5.3 A 105, steady pressure distributions and force measurements were conducted. The study predicted effects of spoiler location, dimensions, and setting angles on lift, drag,, pitching moment coefficients, centre of pressure and aerodynamic, centre in a wide range of angles of attack. Obtained experimental results were compared with results of two theoretical methods based on linearized potential flow theory'(LPT),and wake source model for airfoils with separated flow (WSM), respectively. The study helped in clarifying the flow nature of the airfoil spoiler combination, understanding effects of spoiler on airfoil aerodynamic charac-teristics, and checking the relevant computational codes.