Abstract
A method of unstructured dynamic overset grids is developed for the numerical simulation of helicopter unsteady rotorairframe aerodynamic interaction. For the effective treatment of the relative motion between the rotor and the airframe, the domain of flowfield is divided into two overset subzones, namely, a rotational subzone containing the blades and a stationary subzone containing the airframe. The overset part of two subzones is used to convect the flow variables of the two zones. The Taylor series expansion is used to obtain a second-order spatial accuracy, and dual-time stepping is adopted to improve the solution accuracy. Mesh deformation from the blade motion in forward flight is treated by using a spring analogy. Validation is made by numerically simulating the flows around a wind tunnel configuration and comparing the predicted time-averaged and instantaneous inflow and airframe surface pressure distributions with the experimental data. It shows that the present method is efficient and robust for the prediction of complicated unsteady rotor-airframe aerodynamic interaction phenomena. unstructured grid, overset grids, rotor-airframe interaction, spring analogy, relative motion
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
