English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Zendy Plus

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Zendy Tools

Zendy Open

In this paper high-order high-fidelity simulations of unsteady flows over flapping wings are examined. The numerical framework for the present computational flapping wings analysis is based on the high-order spectral difference (SD) scheme and a mesh deformation algorithms. The resulting method is capable of performing accurate and efficient simulations for unsteady flows over unsteady moving surfaces. This is demonstrated through several numerical experiments with increasing complexity in geometries and flow physics. The problems being studied include three-dimensional flows over an Eppler61 airfoil over a range of angles of attack at transitional Reynolds number of 46, 000, and flows over an oscillating NACA0012 airfoil at Reynolds number of 40, 000. In both cases three-dimensional simulations of the two-dimensional airfoils have been carried out. The numerical solver is finally applied to perform a three-dimensional flapping wing simulation of flows over a semi-complex wing-body configuration.

Towards Computational Flapping Wing Aerodynamics of Realistic Configurations using Spectral Difference Method