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Back pressure dramatically drops with altitude, which substantially affects the 2-stroke Unmanned Aerial Vehicle (UAV) engine's performance. This research involves looking into potential geometry changes that could lead to optimal back pressure values for a two-stroke UAV engine operating at a height of 13,000 feet. The 10,000 feet original geometry is modified in a few different places. The original purpose of the exhaust system was to gather combustion chamber exhaust gases and reject them to the atmosphere while reducing noise. Since four-stroke engines have a separate exhaust stroke, backpressure should be kept to a minimum for optimal engine performance. The back pressure value is calculated using the CFD approach at sea level. CFD analysis is done using ANSYS 2024R1's Fluent module. The k-ε model was selected for the solution setup. The operating pressure was selected at the outlet and velocity was selected at the inlet in boundary conditions. To investigate the trend of varying geometries, simulations are run several times for each altered geometry. It is found that, by increasing the Baffle plate hole diameter the backpressure is reduced and vice versa. By increasing the specific portion of the header pipe (SPHP) length the backpressure is decreased while by decreasing the SPHP length the backpressure is increased. Similarly, with the increase of the diameter of SPHP, the backpressure is enhanced. Moreover, with the decrease of the diameter of SPHP the back pressure is reduced and by increasing the number of holes in baffle plates the back pressure decreases and vice versa.

Keywords: Unmanned Aerial Vehicle, Computational Fluid Dynamics, Exhaust System, Header Pipe Length, Header Pipe Diameter, Specific Header Pipe, Baffle Plates.

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