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compared to perfect gas results is observed. Beneficial effects deriving from the use of a dense working fluid are also observed when the aerodynamic performance of viscous turbulent airfoil flows at large Reynolds number and transonic speeds is considered. The nonclassical variation of the Mach number with density favourably affects the boundary layer development, contributes to reducing friction drag and to avoiding boundary layer separation due to large adverse pressure gradients. Specifically, post-shock separations due to shock/boundary layer interaction are suppressed or greatly reduced, which ensures satisfactory lift and aerodynamic efficiency at flow conditions where the aerodynamic performance of perfect gas flows suffers from shock stall. A shape optimization has been performed for inviscid transonic flows of dense gases over airfoils. Optimal airfoil shapes have been generated by using a multi-objective genetic algorithm coupled with an dense gas flow solver. Though computationally intensive, genetic algorithms are well adapted to the solution of multi-point optimization problems that arise naturally in dense-gas aerodynamics and allow generating airfoil shapes that ensure good performance over a large range of operating conditions. When solved for inviscid flow, the drag minimization problem of a symmetric airfoil with fixed thickness- to-chord ratio yields indeed shock-free shapes for an extended range of freestream Mach number; however, the optimal airfoils display a thick trailing edge that is bound to induce premature flow separation hence an increase in form drag when taking into account the viscous effects in the flow analysis. This point was actually checked by a posteriori numerical experiments using an available version of the SGS solver extended to the Reynolds-Averaged Navier-Stokes equations for dense gas flows. The multi-point performance optimization for a lifting airfoil in subcritical and supercritical flow conditions has allowed determining an airfoil shape that provides an overall improvement of the lift coefficient while preserving the high lift-to-drag ratio typical from BZT flows. However, in the case of inviscid flow optimization, it was again necessary to select an optimum shape within the optimal Pareto set that might ensure good performances also for viscous flows, thanks to a not-too-thick trailing edge, less prone to boundary layer separation. 117PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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