Toward Vehicle-Level Optimization of Compound Rotorcraft Aerodynamics

This paper presents high-fidelity and simplified computational fluid dynamics modeling approaches within an optimization framework for compound rotorcraft configurations with rotor/propeller aerodynamic interactions. Simulations of axial-flight ducted propeller a rotor/wing test case are first presented to validate the in-house Helicopter Multi-Block 3 solver assess actuator disk/line models main rotor modeling. The then used represent simulations generalized combination. performance is analyzed in detail, large variations observed single blade loading due wake. A model interaction simulation also put forward, inflow distortion metric proposed quantify With help kriging surrogate metric, interferences through disk quantitatively visualized position, thrust, advance ratio. Optimization position under minimized interference rolling/pitching moment constraints attempted using both gradient-based (adjoint) gradient-free (efficient global optimization) approaches. results verified resolved simulations, fluctuations were effectively reduced optimization. work step toward methods vehicle configuration