Abstract: “This is a space era for unmanned aerial vehicles (UAVs) with complex autonomous systems to have an objective research on interplanetary studies. The UAV design for the space application is a complicated approach due to its involvement with initial conditions such as the atmospheric data of that particular planet and in later stages, where the experimental testing setup requires a separate infrastructure to match that atmospheric conditions. So, where the planetary data required for design are density, temperature, viscosity, pressure and gravity. These are initial conditions which affects the design and performance parameters in the conceptual stage of the planetary UAV. This paper describes the UAV conceptual design methodology for the Mars application which includes the configuration selection, sizing, aerodynamic analysis and performance evaluation using low fidelity tools such as XFLR5 and OCTAVE (Low order code). The design performance is compared with Earth atmosphere and Martian”

Keywords: Conceptual design, Aerodynamics, Peformance, Space application, UAVs, XFLR5, OCTAVE, Martian atmosphere,VLM, Low fidelity tools, space drones, Sky Walker X8, Wind tunnel Data.