Simulation of flow around oscillating rotor blade section with aeroelastic flap

Flows around rotor blade sections equipped with active flaps with a degree of freedom in the flap deflection angle are considered in this paper. Results for oscillating flaps are presented. The resultant flap motion was found to couple with the unsteady air loads for cases of blade section in oscillatory translation

Exploring the detached-eddy simulation for main rotor flows

This paper applies the Detached-Eddy Simulation (DES) method to resolve a larger part of the flow spectrum around rotor blades in hover and forward flight. A comparison between DES and Unsteady Reynolds–Averaged Navier–Stokes simulation was carried out for the case of a forward flying rotor suggesting that DES has great potential for rotor applications

CFD investigation of a complete floating offshore wind turbine

This chapter presents numerical computations for floating offshore wind turbines for a machine of 10-MW rated power. The rotors were computed using the Helicopter Multi-Block flow solver of the University of Glasgow that solves the Navier-Stokes equations in integral form using the arbitrary Lagrangian-Eulerian formulation for time-dependent domains with moving boundaries. Hydrodynamic loads on the support platform were computed using the Smoothed Particle Hydrodynamics method. This method is mesh-free, and represents the fluid by a set of discrete particles. The motion of the floating offshore wind turbine is computed using a Multi-Body Dynamic Model of rigid bodies and frictionless joints. Mooring cables are modelled as a set of springs and dampers. All solvers were validated separately before coupling, and the loosely coupled algorithm used is described in detail alongside the obtained results

Hybrid Turbulence Models Evaluation for Rotorcraft Flows

No abstract available

Aeroelastic CFD Computations for Rotor Flows

No abstract available

Mesh deformation method for rotor flows

Helicopter blades experience large in-flight deformations that affect the aerodynamics of the rotor. Consequently, computational fluid dynamics (CFD) methods applied to helicopter flows must have appropriate algorithms to account for the blade deformation without deterioration in the CFD mesh quality. In this work, a hybrid mesh deformation method, suitable for use with helicopter blades, is proposed. The method begins by accounting for the blade deformation using a modal structural model. The interpolation between the finite element and CFD meshes for the blade surface is based on the constant-volume tetrahedron method and is combined with transfinite interpolation as well as the spring analogy method. The final algorithm is efficient and resulted in deformed meshes with good qualities. A range of rotor cases were considered, and the changes in volume of the CFD cells were less than 30% of their original values. The cell skewness was also kept at acceptable levels. The mesh deformation method was coupled with the helicopter multiblock CFD solver, and computations were undertaken for rigid and deformed blades. It was found that the structural deformation affected the blade loads even for hovering rotor cases, although it had a more pronounced effect in forward flight. The mesh method was efficient and accounted for less than 1% of the total central processing unit time

The HiPerTilt Project: Developing New Aerodynamics Methods Adapted for Tilt Rotor Aircraft

No abstract available

Aeroelastic Computations of Flapped Rotors

No abstract available

The HiPerTilt Project: Developing New Aerodynamics Methods Adapted for Tilt Rotor Aircraft

No abstract available

Understanding Store Loads using DES and Strongly-Coupled Aeroelastic Simulations

No abstract available