This study aims to investigate the effect of chord ratio of a tandem wing configuration in a transonic, low Reynolds number regime similar to Martian atmospheric conditions. Using ANSYS Fluent 2023 R1 software, a steady, two-dimensional flow study was conducted by varying the chord ratios of a tandem wing setup of two Ishii airfoils. A low Reynolds number of 2.3E + 04 and a transonic Mach number of 0.83 is used for this study. In the CFD simulations, a stagger of 1.5 s/c and a gap value of 0 g/c was used. The decalage angle and the angle of attack were maintained at 0 degrees. Furthermore, the impact of chord ratios, specifically 0.3, 1, and 1.8, (signifying typical canard, tandem wing, and conventional tail configurations) are investigated. An unstructured mesh with a structured layer near the wall is used to capture near wall boundary layer effects. It was observed that with an increase in chord ratio, the overall aerodynamic efficiency seems to increase and so the conventional tail and tandem configurations tend to have better aerodynamic efficiency than the canard configuration. Further, the fore airfoil of the canard configuration and aft airfoil of the conventional tail configuration seem to have aerodynamic efficiencies which are less than that of a single isolated airfoil. No flow separation is observed in all the three configurations at 0 degrees angle of attack. These results show interesting interactions between the fore and aft airfoils in the low Reynolds number transonic regime.