Modified Rotor Blade

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A recent journal article titled "Numerical Investigation of the Effect of Leading-Edge Tubercles on Propeller Performance" can be found at this link: https://arc.aiaa.org/doi/10.2514/1.C034845. Alternatively, you may access it through this publication: http://www.iaeng.org/publication/WCE2018/WCE2018_pp586-595.pdf. If you have any questions or need further information, please don't hesitate to ask. In a recent aerodynamics entry, a rotor blade similar to the one used for the RAH-66 was studied. The cross section of these blades is NACA 9410. Based on the results of a Rear Wing analysis (with dimensions comparable to Formula One), an amplitude of tubercles of 20% of the chord length was chosen. A basic CFD analysis showed significant improvement in thrust-to-torque ratio for the modified rotor compared to the baseline model. The modified rotor produces more thrust at a lower rpm and requires less torque from the engine. Both rotors are 9.9 inches in diameter, with baseline model files available for further analysis if needed. Due to lack of access to a 3D printer, the model can be printed in three parts and joined using adhesive, taking advantage of its circular symmetry. Additionally, consider these entries, which apply the same aerodynamic principles to different areas: Modified Helical Darrieus Wind Turbine Blade, Rear Wing (Formula One dimensions), and Modified 10x4.7 Propeller.