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minimization problem of a symmetric airfoil with fixed thickness-to-chord ratio yields indeed shock-free shapes for an extended range of the freestream Mach number; however, the optimal airfoils generated by neglecting viscous effects display a thick trailing edge that is bound to induce premature flow separation hence an increase in form drag when taking into account the viscous effects in the flow analysis. Moreover, they are also characterized by a thick leading edge, which produces a deep suction peak followed by an extended region characterized by strong adverse pressure gradient. As a consequence, at subcritical speeds these airfoils display a slightly higher drag coefficient than the baseline configuration. These difficulties are overcome by including viscous effects into the optimization process, which provides an airfoil shape whose performance is far superior to the baseline over the whole range of Mach numbers considered for the study. The multi- point performance optimization for a lifting airfoil in subcritical and supercritical flow conditions has allowed determining an airfoil shape that provides an overall improvement of the lift coefficient while preserving the high lift-to-drag ratio typical from BZT flows. This results will be widely presented in Chapter 4. Finally, in [47], Congedo & Cinnella & Corre present a study about optimal blade shapes for BZT ORC turbines, providing high efficiency over a large range of operating conditions and working with high cascade pressure ratios. But, for the high cascade pressure ratio considered in this study, BZT effects play a minor role in efficiency improvement. The use of properly designed turbine cascades working with somewhat lower pressure ratios could allow higher efficiency improvements due to BZT effects, opening the door to the development of BZT turbines for Organic Rankine Cycles. The results in [47] are widely presented in Chapter 4. 1.1.3. GA-Hardness of Dense gas Flow optimization problems In spite of the increasing success of GAs for aerodynamics applications, no systematic studies of their convergence properties for aerodynamic problems of interest exist. Specifically, information lacks about how the flow-physics of a given problem affects the objective function, and hence, GA convergence. An objective function is informally defined to be GA-hard when a GA cannot detect an optimum within a reasonable number of iterations. One of the major causes of GA-hardness is the strong coupling in the objective function among different components of the high-dimensional search space. This phenomenon is termed epistasis. Epistasis variance, introduced by Davidor [58] in 1991, is a measure for the GA-hardness of a function and has been used to predict the performances 29PDF Image | ANALYSIS AND OPTIMIZATION OF DENSE GAS FLOWS: APPLICATION TO ORGANIC RANKINE CYCLES TURBINES
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