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- W2107730758 abstract "The numerical optimization of thick airfoils by means of genetic- and gradient-based numerical optimization in combination with a Navier–Stokes code is described and the results are discussed. The objectives of the study are to maximize both the section moment of inertia, and the airfoil lift-to-drag ratio at fully turbulent conditions and a chord Reynolds number of 1 10 6 . A robust and flexible airfoil surface definition that is based on polynomial functions and allows for blunt trailing edges is used to generate section shapes with a maximum-thickness-to-chord ratio between 35 and 42%. To mitigate the unsteady vortex shedding, a splitter plate is added to the blunt trailing edge of the resulting airfoils. This allows steady-state simulations with the Navier–Stokes code and reduces the calculation time. The study resulted in a Pareto front, which represents a range of aerodynamically and structurally improvedairfoils.Althoughtheoptimizerwasgiventheopportunitytocreateairfoilswithanominallysharptrailing edge, the improved airfoils all contain significant trailing-edge thickness." @default.
- W2107730758 created "2016-06-24" @default.
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- W2107730758 date "2007-01-01" @default.
- W2107730758 modified "2023-10-17" @default.
- W2107730758 title "Design and Numerical Optimization of Thick Airfoils Including Blunt Trailing Edges" @default.
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- W2107730758 doi "https://doi.org/10.2514/1.23057" @default.
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