A reverse approach has been followed to handle the problem of investigating the aerodynamic characteristics of a typical unmanned aerial vehicle model which are assumed unknown. Both numerical and experimental investigations have been conducted using wind tunnel and CFD facilities. The tests have been conducted in a low speed wind tunnel for a half section of real size tailless model. The aerodynamic loads have been measured and the loads were varied with pitch performed in range of (-2 to +26°) angles of attack with pre-selected test wind speeds between (25 – 40) m/s. The test was carried out with different elevon deflection angles selected as (0-10-20-30°). The pressure tabs to investigate the chord-wise pressure distribution at Mean Aerodynamic Chord (MAC) for the sake of comparison between wind tunnel and CFD results. The test section conditions have been taken as inputs for the simulation with CFD Fluent software. Results revealed that the model was statically stable and the variation of aerodynamic coefficients to wind speed, angle of attack and elevon deflection is displayed. The pressure distribution along the MAC demonstrated the expected behaviour of the chord-wise pressure distribution during stall and laminar flow around the airfoil.