Abstract
Maintaining a steady hover flight in a rotorcraft usually requires high energy input. The aim of the paper is to prove that it is possible to vastly reduce energy use in a rotorcraft by reducing the disc loading. The energy consumption reduction is especially important in electric rotorcraft, where the energy source is characterized by low energy density when compared to the hydrocarbon fuel in ICE rotorcraft. The paper presents results of CFD simulations on low Reynolds Number operating rotors. For low RE rotors tip vortex induced drag is highly affecting the rotor’s Figure of Merit, thus reducing rotor performance. Even though FM is reduced, the low RE setup is still beneficial in terms of reduced Power Loading, the main factor responsible for hover endurance.
Highlights
Over the years the rotor performance was being improved making rotorcraft a safe and competitive form of transportation
Results prove the feasibility of low Reynolds Number at low Disk Loading as plotted on Fig. 3
The results from theoretical model, Blade Element Theory (BET) analysis and CFD analysis prove that using low RE rotor blades is achievable
Summary
Over the years the rotor performance was being improved making rotorcraft a safe and competitive form of transportation. We can decrease PL by decreasing the Disk Loading, increasing the Figure of Merit or using the forward flight induced power benefits. In this paper [3] author developed a model for flapping flight if birds and insects – one scenario of low Reynolds Number hovering flight. Another model for low-RE flight conditions can be found here [4]. The aim of this paper is to find out the feasibility of using low-RE rotor conditions in hover flight in order to reduce the power needed by the rotorcraft. There is lack of papers analysing low-RE rotor conditions at larger rotor diameter scales (> 0.5m)
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