The flow and flame dynamics within liquid fueled gas turbine combustors are complex due to the interactions between the highly turbulent flow, spray dynamics and combustion. Computational tools help understand these governing processes. A computational fluid dynamics model for Army Research Combustor Midsize (ARC-M1) is developed to characterize the complex turbulent flow, multi-phase spray physics and hydrocarbon chemistry. Using high-quality X-ray data for the combustor, the spray is initialized in the near nozzle region. To understand the overall impact of liquid properties, the liquid properties corresponding to Jet-A and F-24 are tested. It is observed that F-24 has a higher LBO liquid flow rate compared to Jet A. To understand the impact of individual properties, liquid properties such as density, viscosity, specific heat, heat of vaporization, are changed one at a time. It was observed that an increase in density, viscosity, heat of vaporization and specific heat w.r.t Jet-A tends to increase the LBO liquid flow rate i.e. makes the flame blow-off at higher equivalence ratios. This is attributed to the altered flame shapes and the impact of these properties on fuel heating and its subsequent vaporization.