Unsteady airfoil flow solutions on moving zonal grids
Cricelli, Antonio M.
Ekaterinaris, John A.
Platzer, Max F.
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Subsonic and transonic steady and unsteady flowfields over airfoils are investigated with the numerical solution of the governing equations. This study aims to enhance the performance of rotary wing and fixed wing aircraft by better understanding and by taking advantage of unsteady phenomena such as dynamic lift. In the past few years many advances have been made in algorithm development for the numerical solution of the Euler and the Navier-Stokes equations. In this study, these new zonal techniques are applied. A zonal approach is more computationally efficient in solving the governing equations than previous approaches, and has certain advantages over the standard single moving grid approach. The zonal grid consists of two grids, one being the inner grid which is fixed to the airfoil, and the other being the outer grid which extend to the far field or to a specified outer boundary. The inner grid is allowed to rotate with the body, while the outer grid remains fixed. The thin-layer Navier-Stokes equations are solved for the inner grid, while the Euler equations are solved for the outer grid. Communication between the two grids is accomplished by interpolating the flow quantities at the zonal interface. Solutions are obtained for flows at fixed angles of incidence, and for unsteady flows over pitching and oscillating airfoils. The computer results are in good agreement with available experimental data.
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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