This paper proposes an analytical model that calculates various flight parameters, such as peak maximum range for pre-determined configurations based on pre-built systems by the research group. The model serves as a tool to compare different turboelectric systems with respect to flight operability and assist in determining an optimal configuration for a select mission flight. This tool performs calculations with user inputs of leg type and altitudes, and battery specifications of capacity, voltage, and discharge rate. Calculations follow basic aerodynamic principles and relations to acquire other flight characteristics such as velocity, fuel burn, and rate of climb
