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Figure 32: Lifting airfoil 2-point performance optimization. Wall distributions (a) of the pressure and skin friction (b) coefficients for viscous flow at OP#1 past the NACA0012 airfoil and an optimal airfoil for DG flow. ..........................................................................88 Figure 33: Lifting airfoil 2-point performance optimization. Wall distributions (a) of the pressure and skin friction (b) coefficients for viscous flow at OP#2 past the NACA0012 airfoil and an optimal airfoil for DG flow. ..........................................................................89 Figure 34: Evolution of the maximal and mean value of the drag coefficient for the computed population as a function of the number of generations.......................................93 Figure 35: Geometry of minimal drag airfoils obtained by including or neglecting, respectively, viscous effects, and NACA0012 airfoil..........................................................93 Figure 36: 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) NACA0012 perfect gas; B) NACA0012 dense gas; C) Shape optimized for viscous dense-gas flow; D) Shape optimized for inviscid dense-gas flow; M∞=0.96, Re≈107. ................................................................................................................................94 Figure 37: Wall distribution of the pressure coefficient for three cases plotted in Figure 36 ............................................................................................................................................. 95 Figure 38: Drag coefficient as a function of the freestream Mach number for dense-gas viscous flow at operating conditions p∞/pc=0.985, ρ∞/ρ c=0.622. The figure compares the performance of an airfoil shape optimized for viscous dense gas flow, for an airfoil shape optimized for inviscid dense gas flow, and for the NACA0012 airfoil...............................95 Figure 39: Lifting airfoil 2-point performance optimization. Overview of the computed solutions during the genetic evolution process....................................................................99 Figure 40: Optimal airfoil shapes and baseline shape for the lifting flow problem. ...........99 Figure 41: Mach number contours and flow streamlines for Airfoil 4 (A), Airfoil* (B) and the NACA0012 airfoil (C). M∞=0.85, =1°, Re=9×106. Left: condition OP1; right: condition OP2. ................................................................................................................... 100 Figure 42: Wall distributions of the pressure coefficient Cp for Airfoil 4, Airfoil*, and NACA0012. M∞=0.85, α=1°, Re=9×106. A) Condition OP1; B) condition OP2. ........... 101 Figure 43: optimal shape for perfect gas flow ................................................................... 104 Figure 44: optimal shape for dense gas flow ..................................................................... 104 Figure 45: PFG flow, isoMach lines: a) baseline; b) optimized. c,d) Wall distributions. . 105 15PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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