This study was designed to explore the influence of different configurations of Cessna 172R wing geometry on its performance output. Accordingly, this modification emphases on the wing chord and wingspan with host parameters (aspect ratio and taperness ratio). However, the given National Admonitory Committee of Aeronautics standards (NACA 2412) is not changed. Moreover, analytical, computational and experimental approaches wear employed with the help of a classical theory, design foil software and wind tunnel experiments respectively. The findings of the study indicated that the modified wing span enhances the performance output of the aircraft. However, the modified wing chord has a negative impact on the performance output. More specifically, the lift coefficient, range, and endurance of the modified wingspan were improved up to 14.84%, 22.46% and 27.72% correspondingly. While the chord length increases the drag coefficient increases up to 15.15% on the performance output. As a result, the modified wing span has an optimum fuel consumption rate.