High fidelity CFD/CSD method for rotor blade optimization

This paper demonstrates a framework for using high-fidelity methods to design rotor blades. An initial rectangular blade is optimised with respect to a generalised blade surface parameterisation, which includes variations in twist, chord, sweep and anhedral. Particular focus is placed on coupling aeroelasticity with the adjoint optimisation and trimming methods at desired flight conditions. Conclusions are drawn on the new design’s effectiveness and the framework’s efficiency to obtain it. The obtained design featured a twist distribution balancing hover and forward flight performance, with a tip design needed to alleviate adverse effects in forward flight. Prominent features include forward and aft tip sweeps with a small reduction in chord distribution.