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Figure 19: Evolution of the maximal and mean value of the drag coefficient for the computed population as function of the number of generations. Mono-objective (single operation point) optimization runs for different values of the freestream Mach number....73 Figure 20: Geometry of optimized airfoils, sonic arc, Rusak low-drag airfoil and NACA0012 airfoil. .............................................................................................................. 74 Figure 21: Pressure drag verus free-stream Mach number for different airfoil shapes. Results obtained using UGS (a) and SGS (b)......................................................................75 Figure 22: Wall pressure (a) and Mach number (b) distributions for optimized airfoils, sonic arc, Rusak airfoil and NACA0012 airfoil at M=0.95. SGS results............................76 Figure 23: (a) optimal geometries for the drag minimization problem solved in the case of a PFG flow and a DG flow with VDW or MAH EOS. (b) Associated pressure drag as a function of the freestream Mach number.............................................................................77 Figure 24: Pressure contours around the baseline NACA0012 airfoil and optimal airfoils for perfect and dense gas flows with freestream conditions leading to an equivalent amount of wave drag for the baseline airfoil. ................................................................................... 78 Figure 25: Mach number contours and streamlines for turbulent flows past four airfoils (right); left: close-up of the streamlines at the trailing edge (grid aspect ratio not preserved). A) OAB; B) OA095; C) NACA0012; D) Rusak-Wang. M ∞ = 0.96, Re ≅ 107 . ............................................................................................................................................. 79 Figure 26: Viscous performance of minimal-drag airfoils stemming from inviscid optimization. ........................................................................................................................ 80 Figure 27: Lifting airfoil 2-point performance optimization. Overview of the computed solutions during the genetic evolution process....................................................................84 Figure 28: Lifting airfoil 2-point performance optimization. Typical optimal shape. ........84 Figure 29: Lifting airfoil 2-point performance optimization. Wall distributions (a) (b) at OP#1 for the NACA0012 airfoil and an optimal airfoil for DG flow. ................................85 Figure 30: Lifting airfoil 2-point performance optimization. Wall distributions (a) (b) at OP#2 for the NACA0012 airfoil and an optimal airfoil for DG flow. ................................86 Figure 31: Evolution of aerodynamic performances (a) (b) at M∞=0.85 and α =1° for a dense gas flow around the NACA0012 airfoil and a DG-optimized airfoil at different free- stream thermodynamic conditions.......................................................................................87 14PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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