Shahrood University of Technology Journal of Solid and Fluid Mechanics 2251-9475 15 1 2025 03 21 Comparative Analysis of Electro aerodynamic Propulsion and Electric Motors for the Zephyr 8 UAV Comparative Analysis of Electro aerodynamic Propulsion and Electric Motors for the Zephyr 8 UAV 19 31 3482 10.22044/jsfm.2025.15524.3926 FA Alireza Ahmadi MSc student, Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran Rouhollah Khoshkhoo Assist. Prof., Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran Mehran Nosratollahi Assoc. Prof., Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran Journal Article 2025 01 03 Electroaerodynamic propulsion is a thrust-generation technology that has gained significant attention in recent years. This study explores the advantages, disadvantages, and challenges of developing this propulsion system. Additionally, it compares the performance of electroaerodynamic propulsion with an electric propulsion system for the Zephyr 8 UAV.A mathematical model for the electric motor is presented, and performance charts are generated using data from the Zephyr 8 aircraft. Subsequently, a mathematical model for the electroaerodynamic propulsion system is developed. Using a hybrid GA-SQP optimization algorithm, an optimized design for the electro aerodynamic motor is created to achieve thrust comparable to the electric motor at an altitude of 21,000 meters and a flight speed of 10 m/s. Performance charts for the electro aerodynamic motor are also generated and analyzed. A comparison of the two systems indicates that aerodynamic ion propulsion could serve as a viable alternative to electric motors for the Zephyr 8 UAV, offering potential benefits in energy efficiency and high-altitude performance. Electroaerodynamic propulsion is a thrust-generation technology that has gained significant attention in recent years. This study explores the advantages, disadvantages, and challenges of developing this propulsion system. Additionally, it compares the performance of electroaerodynamic propulsion with an electric propulsion system for the Zephyr 8 UAV.A mathematical model for the electric motor is presented, and performance charts are generated using data from the Zephyr 8 aircraft. Subsequently, a mathematical model for the electroaerodynamic propulsion system is developed. Using a hybrid GA-SQP optimization algorithm, an optimized design for the electro aerodynamic motor is created to achieve thrust comparable to the electric motor at an altitude of 21,000 meters and a flight speed of 10 m/s. Performance charts for the electro aerodynamic motor are also generated and analyzed. A comparison of the two systems indicates that aerodynamic ion propulsion could serve as a viable alternative to electric motors for the Zephyr 8 UAV, offering potential benefits in energy efficiency and high-altitude performance. https://jsfm.shahroodut.ac.ir/article_3482_2534a18e6c4c661549a663ebcbcbcb32.pdf