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Abstract
This paper presents the preliminary results from the experimental study of the aerodynamic characterization of a novel dissimilar coaxial rotor concept with reduced rotor-rotor interaction. The performance of dissimilar coaxial rotor concept is compared with existing rotor configurations such as conventional single main-rotor tail-rotor and regular coaxial rotor. The performance measurement is carried out using a small scale coaxial hover test stand facility setup for this purpose. The hover performance of different rotor concepts namely conventional, regular coaxial and dissimilar coaxial rotors are compared as anti-torque mechanisms with same baseline rotor by comparing their power loading. The inter-rotor spacing between coaxial rotors is kept constant at 15% of the rotor radius. The dissimilar coaxial rotor appears to be a promising solution for development of high efficiency hovering rotor system for high thrust condition. From the tests conducted on a main rotor of 0.415 m radius operated at 1000 RPM, it is established that the dissimilar coaxial rotor system consistently shows higher power loading than the conventional rotor (especially at high thrust condition) as well as the coaxial rotor system. To achieve maximum benefits from the dissimilar coaxial rotor system, the anti-torque rotor in the dissimilar rotor pair must be spun at 50% or 40% of the main rotor RPM. The effect of the cross-section shape of the blade-hub attachment (root cutout) plays a significant role in reducing the profile power loss of the anti-torque rotor of the dissimilar coaxial rotor. In the current study, three different shapes were compared and the elliptical cross-section shape was observed to give best performance.

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  Performance Measurement of a Novel Dissimilar Coaxial Rotor System

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