Experimental evaluating approach to a suitable Martian coaxial rotorcraft blade

This paper presents a detailed experimental approach for understanding and optimizing the hover performance of Martian UAV rotor, including a systematic discussion about several coefficients for hover characteristics and a detailed design approach for rotor blades of Martian UAV at Reynolds numbers lower than 50000. The discussed hover performance coefficients include figure of merit, thrust coefficient, thrust weighted solidity, power loading and disk loading, and these coefficients are also used to evaluate the hover performance of a specific rotor configuration. In addition, rotor parameters are investigated and analyzed in this experimental approach, including airfoil, camber, solidity, blade chord, number of blades and blade twist. These parameters are the major factors significantly influence the rotor hover performance. A detailed rotor design approach is proposed based on the experimental result by optimizing the hover performance coefficients and rotor parameters.

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