Abstract
In the present work, the aerodynamic performance of the Caradonna and Tung and S-76 in hover were investigated using a simplified concept of multiple reference frame (MRF) technique in the context of high-order Monotone Upstream Centred Scheme for Conservation Laws (MUSCL) cell-centred finite volume method. In the present methodology, the frame of reference is defined at the solver level by a simple user input avoiding the use of mesh interface to handle the intersections between frames of reference. The calculations were made for both out-of-ground-effect (OGE) and in-ground-effect (IGE) cases and compared with experimental data in terms of pressure distribution, tip-vortex trajectory, vorticity contours and integrated thrust and torque. The predictions were obtained for several ground distances and collective pitch angle at tip Mach number of 0.6 and 0.892.
Highlights
The helicopter is known by its wide versatility of flight condition with distinctive ability to take off and land from almost any place
This is important on the design concept of the helicopter or drones and on noise and safety of the surrounding. Accurately predicting this vortex dominated flow-field and aerodynamics is a difficult task for most commercial Computational Fluid Dynamics (CFD) codes since higher-order resolution is almost requirement [2]
In order to provide a strong level of correlation between the prediction and experimental, the accuracy of the developed framework is evaluated on two distinct hovering rotorcraft flow cases: Fig. 3
Summary
The helicopter is known by its wide versatility of flight condition with distinctive ability to take off and land from almost any place. Chen-Long et al [23] assessed the capability of the Overset and other methods such as sliding-mesh and moving reference frame to perform a low-order simulation of the hovering Caradonna and Tung rotor. These methods were compared in terms of velocity and pressure field and differences were pointed in terms of accuracy, mesh and convergence time. In order to avoid this non-physical mesh interface, Remaki et al [30] proposed a simplified technique to virtually split the domain This approach was implemented o on the second-order cell-vertex based CFD code, SU 2, and compared with experimental and commercial software for 2D and 3D cases. The OGE and IGE predicted results of the rotor aerodynamic performance of S-76 [51] rotor are compared with experimental data in terms of collective blade pitch, thrust and torque
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