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to be sufficiently far from the thermodynamic critical point, so that dense gas effects such as dramatic variations of the fluid specific heat and compressibility can be neglected; in these conditions, density fluctuations will not be as huge as in near-critical conditions and subsequently the turbulence structure will not be affected significantly; (b) at least for equilibrium boundary layers, the mean flow behavior can be predicted adequately using RANS completed by an eddy viscosity turbulence model; similarly, the turbulent heat transfer can be modelled through a ”turbulent Fourier law”, as usual for PFG flows, where the turbulent thermal conductivity is computed in a classical way by introducing a turbulent Prandtl number, assumed to be roughly constant and O(1) throughout the flow. Hypothesis (a) is justified by the fact that the flows of interest for this study actually do not evolve in the immediate neighborhood of the critical point; and in fact, if inviscid analyses and computations show an uncommon variation of the fluid speed of sound (and hence compressibility) with pressure perturbations, nevertheless the magnitude of these variations is approximately of the order of those occurring in perfect gases. Moreover, peculiar dense gas phenomena related to flow heating or cooling are excluded from considerations, since the airfoil wall is supposed to be adiabatic. On the contrary, Hypothesis (b) should be considered with some caution. On the one hand, if Hypothesis (a) is verified, it seems quite reasonable to apply to compressible dense gas flows turbulence models initially developed for incompressible flows of perfect gases and currently extended in the common practice to compressible PFG flows; on the other hand, more or less strong pressure gradients and shock waves characterizing the outer inviscid flow are likely to affect the boundary layer, which can no longer be considered an ”equilibrium” one; this is also true for the reference PFG flows considered in the study, characterized by strong shock waves and shock/boundary layer interactions. Thus, aerodynamic performance predictions will necessarily be affected by deficiencies inherent with the chosen turbulence model. Nevertheless, since investigations are intended to provide trends of behavior more than accurate values of the computed aerodynamic coefficients, use of hypothesis (b) represents a means of obtaining preliminary information about realistic dense gas flows with a reasonable computational expense. Specifically, present results have been obtained using the simple algebraic model of (Baldwin & Lomax 1978), whose deficiencies in nonequilibrium boundary layer are well known (see for example [63], for a wider discussion): for example, flow features such as the location of shock waves and the length 33PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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