Modified Rotor Blade

grabcad

Relevant journal article "Numerical Investigation of the Effect of Leading-Edge Tubercles on Propeller Performance" Read More: https://arc.aiaa.org/doi/10.2514/1.C034845Relevant publication: http://www.iaeng.org/publication/WCE2018/WCE2018_pp586-595.pdfDM for any further questions.This is not an improvement over the RAH-66 rotor blades, the black rotor is more efficient than white rotor.Another entry from the aerodynamics. This time a rotor blade, proportionally similar to the rotor blade they used for the RAH-66. The cross section of the blades is NACA 9410.Based on the results of Rear Wing (~Formula One Dimensions), I chose an amplitude of tubercles to be 20% of the chord length. A basic CFD analysis shows a strong improvement in thrust to torque ratio of the modified rotor when compared with the baseline model. The modified rotor produces more thrust at an rpm and requires less torque from the engine to achieve that rpm. The modified rotor produces more thrust at a lower rpm than the baseline model and requires significantly less torque from the engine to achieve that rpm (less rpm).Both of these rotors are 9.9 in in diameter. Baseline model files are also attached, if the anyone/jury wants to run their own CFD analysis.I have no access to a 3D printer, you can print this model in one third and use adhesives to join the three parts, taking advantage of the circular symmetry.Also consider these entries, same aerodynamic principles apply, with entirely different areas of application: Modified Helical Darrieus Wind Turbine Blade, Rear Wing (~Formula One Dimensions) and Modified 10x4.7 Propeller