University of Tehran Press Journal of Computational Applied Mechanics 2423-6713 57 2 2026 04 01 Computational Fluid Dynamics Simulation of Rotor Blade Aerodynamics for the Mars Ingenuity Helicopter 296 325 105750 10.22059/jcamech.2026.410269.1769 EN Alex Miller MPESG, Corrosion Lab, 3-08, Aeronautical and Mechanical Engineering Division, University of Salford, M5 4WT, UK Osman Anwar Bég MPESG, Corrosion Lab, 3-08, Aeronautical and Mechanical Engineering Division, University of Salford, M5 4WT, UK Tasveer Anwar Bég Engineering Mechanics Research, Israfil House, Dickenson Rd., Manchester, M13, UK M.M. Bhatti Department of Physics, College of Science, Korea University, 145 Anam-ro, Seongbuk-gu, Seoul 02841, Republic of Korea Material Science Innovation and Modelling (MaSIM) Research Focus Area, North-West University (Mafikeng Campus), Private Bag X2046, Mmabatho 2735, South Africa Sireetorn Kuharat MPESG, Corrosion Lab, 3-08, Aeronautical and Mechanical Engineering Division, University of Salford, M5 4WT, UK Ali Kadir MPESG, Corrosion Lab, 3-08, Aeronautical and Mechanical Engineering Division, University of Salford, M5 4WT, UK Journal Article 2026 01 29 The Mars Ingenuity helicopter, a coaxial rotor aerial vehicle, is a pioneering venture into extraterrestrial flight. Rotorcraft technology plays a significant role in future mission development, as it offers advantages for specific applications, particularly in rugged terrain or confined spaces. Mars' landscape presents challenges, including unpredictable wind patterns and dust particles. To fly in the thin, predominantly carbon-dioxide-based atmosphere, rotor blades are designed for efficiency in low density environments with a large blade diameter. This work examines the aerodynamic performance of the blade configuration in a quadcopter Mars Ingenuity design using ANSYS FLUENT computational fluid dynamics. A detailed rotor blade model for CFD analysis has been developed for flow behavior around the rotor blades in Mars atmospheric conditions. Data from the Mars 2020 mission and the Mars Ingenuity Helicopter is used as a baseline. Extensive simulations are described for contour plots and flow vectors, focusing on vortex effects and performance in the Mars atmosphere. The study also addresses unsteady airflow around the rotor disk, leading to instabilities such as blade-vortex interactions and retreating blade stall. Future pathways include control aspects of the blade configuration and blade twist. https://jcamech.ut.ac.ir/article_105750_178465e10a628b3b066dc8558967036d.pdf