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- W2016852732 abstract "This study examines an advanced viscous-inviscid interactive method developed for the analysis and design of airfoils in two-dimensional subsonic compressible flow (Ma ∞ <0.4). Inviscid flow is solved with a panel method. The laminar boundary layer is calculated by Thwaites' method. Transition is determined by Michel's relation or the e n method. An integral solution for a turbulent boundary layer is derived from an entrainment equation. Closure conditions are obtained with empirical relations. Singularities near the separation are avoided by inverting the boundary-layer method. Inviscid and viscous flows are coupled with transpiration. The analysis method is used as a black box in the design tasks. The geometry of the starting airfoil is perturbed iteratively by transpiration until the pressure distribution converges to a predefined target This study proposes the necessary degrees of freedom in the target velocity distribution to obtain a closed airfoil. Design cases are included, which support the general applicability and accuracy of the numerical design method." @default.
- W2016852732 created "2016-06-24" @default.
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- W2016852732 date "2006-07-01" @default.
- W2016852732 modified "2023-09-26" @default.
- W2016852732 title "Viscous-Inviscid Method for Airfoil Analysis and Design for Aviation and Windmills" @default.
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- W2016852732 doi "https://doi.org/10.2514/1.17635" @default.
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