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strong suction exerted on the upper surface is the main reason of the dramatic improvement of the lift over the perfect gas for an inviscid flow. The other side of the coin is that, when viscous effects are taken into account, the very strong adverse pressure gradient downstream of the suction peak leads to a significant growth of the boundary layer and to enhanced friction in the leading edge region. Consequently, the peak itself is noticeably smoothed out, and the airfoil lift drops below the inviscid value. Figure 32 shows the wall pressure coefficient and skin friction distribution for this case. For flow conditions OP#2, the relevant differences with respect to inviscid flow are due to strong shock/boundary layer interactions, leading to post-shock separation and reattachment, both in the flow over the NACA0012, and over OAB, with subsequent blow up of the subsonic part of the boundary layer (see wall pressure and skin friction distributions on Figure 33). Paradoxically, in this case the shock/boundary layer interaction leads to a reduction both in lift and drag coefficients with respect to inviscid flow, due to considerably decreased strength of shock waves. For completeness, the PFG viscous aerodynamic performance of the NACA0012 is also included in Table 1: in the PFG case, the lift coefficient is negative, because of massive post-shock separation at the upper surface, caused by severe shock/boundary layer interaction. Case Optimized airfoil, condition OP#1 Optimized airfoil, condition OP#2 NACA0012, condition OP#1 NACA0012, condition OP#2 NACA0012, perfect gas flow CD 1.416x10-2 6.648x10-2 1.275x10-2 3.448x10-2 5.456x10-2 CL CL/CD 0.6077 42.92 0.9693 14.58 0.1833 14.38 0.2529 7.335 -4.086x10-2 -0.7489 Table 1: Aerodynamic performance of viscous flows over the NACA0012 airfoil and an optimized airfoil stemming from the MOGA strategy. 83PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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