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Figure 3: Fundamental derivative versus pressure along selected isentropes. 4.1.2. Inviscid Flow behavior Inviscid flow computations are performed using three C-grids, formed by 136×20, 272×40 and 544×80 cells, respectively. The outer boundary is about 20 chords away from the airfoil and the mean height of the first cell closest to the wall is about 5 × 10−2 chords on the medium grid. For most of the computations presented in the following, grid convergence for the wall pressure and Mach number has been obtained on the medium grid. The reference solution for a perfect diatomic gas (specific heat ratio γ = 1.4) flowing at M∞ = 0.85, α = 1° is first considered (see for details [39]). The flow is characterized by two shocks at about 85% of the chord at the suction side, and 63% at the pressure side. The lift coefficient, drag coefficient, and lift-to-drag ratio computed with the present numerical method on the finest grid are: CL = 0.373; CD = 5.74 × 10−2; CL/CD = 6.51. Then, flows of the dense gas PP10 past the same airfoil are computed. Results obtained for lift, drag, and lift-to-drag ratio for different choices of the free-stream fundamental derivative and free-stream entropy are summarized in Figure 4. For the lowest values of 49PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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