Aydın M.E.Bağcı M.2026-03-102026-03-1020259798331513672https://doi.org/10.1109/ICMAE66341.2025.11277098https://hdl.handle.net/20.500.13091/13078IEEE; Science and Engineering InstituteAirplanes are among one of main vehicles in the aviation sector. Today, these vehicles are used in transportation, military applications and various activities. Mechanical components of vehicles traveling at high altitudes are subjected to harsh operating conditions and technical factors such as material selection and component geometry need to be considered during design. For instance, an airplane at 40,000 feet above ground is exposed to cold ambient conditions with its external components. They also require complex component geometry, light weight and wear resistance. Combining these features expected from working conditions and components in structure, designs of aircraft components are differentiated. In this context, the palaveter component, which plays a critical role in aircraft, takes output power from turbojet engine and generates thrust and traction force, enabling aircraft to hold and advance in air. Aerodynamic effects encountered by aeroplanes and various micron-sized particles in environment cause damage to palaveter wing structure and prevent operation of aircraft. An airplane flies at about -50°C, -60°C and reaches speeds of 800, 900 km/h. Collision with micron-sized hard particles at such high speeds and low ambient temperatures calls into question whether palaveter components will have sufficient mechanical strength. Various design details of the palaveter wing structure should be planned in advance, taking into account aerodynamic effects, cold ambient conditions and operating conditions of the aircraft. In addition, palaveter material selection should also be made according to these effects. In this study, considering the aerodynamic effects and operating temperatures to which the aircraft palaveter components are exposed, effects to which component will be exposed are analyzed with discrete element method (DEM) The design parameters of high and low wing angle, reverse angle, angle of attack and wing ridge of the palaveter wing structure were determined by taking into account the vehicle speed of 800 km/h relative speed, which rotates at 3 different values between 0 - 100 mph. Titanium and aluminum alloys were focused on as palaveter materials, and appropriate material determination was also made and aircraft palaveter design was realized. Crash analyses with micron-sized hard particles were applied to the appropriate designs with discrete element software and it was also investigated that they showed the required strength with the designed working conditions. As a result of lack of resources in literature, a necessary output for designers was created as a result of this study. ©2025 IEEE.eninfo:eu-repo/semantics/closedAccessAerodynamicDesignDiscrete Element MethodPalaveterWearConference Object10.1109/ICMAE66341.2025.112770982-s2.0-105030496035