Numerical simulation demonstrates reduced drag and vibration with increasing blade twist in high-speed lift-offset coaxial rotors, indicating improved aerodynamic efficiency.
Numerical simulations of a lift-offset coaxial rotor with blade twist of 0, 4, and 8 degrees during high advance ratio forward flight are conducted. The coaxial rotor's performance, cyclic controls, blade airloads and hub loads were analyzed using the rFlow3D rotorcraft CFD code with lift-offsets up to 0.3 at high advance ratios (μ = 0.7, 0.3). The results show that as blade twist increases, the increased rotor normal force distribution in the front and rear of the rotor was flattened by the increased normal force near ψ = 90º on the advancing side, and the effective drag coefficient decreases with a decrease in the collective pitch angle. The increase in blade twist is also effective in reducing vibration because it decreases both the blade airloads and the hub loads.
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Akasaka et al. (2025) studied this question.
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