Abstract
This research aims to investigate a virtual blade model and assess rotor influence on helicopter fuselage aerodynamics. The rotor disk is discretized in the azimuthal direction, and a time-varied pressure jump is applied in regions occupied by the blades. To obtain the pressure jump, an actuator disk is employed using uniform and non-uniform blade load distribution, based on momentum theory.
Highlights
Rotor Computational Fluid Dynamics (CFD) calculations are challenging
The complexity of the problem is due to the flow unsteadiness, the coupled aerodynamics and aeroelasticity of rotor blades, and the presence of vortical effects and wakes characterized by a range of flow scales, both laminar and turbulent
Classic actuator disk models allow the use of steadystate CFD computation, significantly reducing the required computer time and memory
Summary
Rotor Computational Fluid Dynamics (CFD) calculations are challenging. The complexity of the problem is due to the flow unsteadiness, the coupled aerodynamics and aeroelasticity of rotor blades, and the presence of vortical effects and wakes characterized by a range of flow scales, both laminar and turbulent. The momentum source is modeled independently of the fuselage without any coupling between the two For this reason, the effect of the rotor disk is simplified and the method, computationally efficient, can only be used for initial estimates of the fuselage loads [3, 4]. The effect of blades on the fuselage is unsteady For this reason the vortical structure of the flow around a fuselage in rotor-body interaction is different than what is predicted by steady-state actuatordisk methods. This problem can be partly solved using. The parameters of turbulence determine the broadband noise of the flow [6]
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