Almost all possible airfoil shapes can be created with these three families allowing for all possible configurations to be included. The increased design space is due to the use of multiple parametric airfoil families, namely the NACA 4 series, CST family, and the PARSEC family. The method proposed is different from prior optimization efforts in that it greatly broadens the design space, while allowing the optimization to search for the best candidate that will meet multiple objectives over a characteristic mission profile rather than over a single condition and single optimization parameter. This thesis proposes an integrated method for analyzing, evaluating, and optimizing an airfoil using a coupled viscous-inviscid solver along with a genetic algorithm to find the optimal candidate. To accomplish this goal, a coupled viscous-inviscid method is used. Therefore, another evaluation method is needed to provide accurate results at a faster pace. However this method can prove to be overwhelmingly time consuming when performing an initial design sweep. To evaluate the aerodynamic performance of a design, viscous Navier-Stokes solvers can be used. Several examples illustrating this method are presented and discussed.Īn Integrated Method for Airfoil Optimizationĭesign exploration and optimization is a large part of the initial engineering and design process. The method is based on the streamline curvature velocity equation. The method uses several existing CFD codes and can design a new airfoil in only a few days using a Silicon Graphics IRIS workstation.Ī streamline curvature method for design of supercritical and subcritical airfoilsĪn airfoil design procedure, applicable to both subcritical and supercritical airfoils, is described. The thrusts of the method are its ability to calculate a target N-Factor distribution that forces the flow to undergo transition at the desired location the target-pressure-N-Factor relationship that is used to reduce the N-Factors in order to prolong transition and its ability to design airfoils to meet lift, pitching moment, thickness and leading-edge radius constraints while also being able to meet the natural laminar flow constraint. Drag reductions have been realized using the design method over a range of Mach numbers, Reynolds numbers and airfoil thicknesses. Mineck, Raymond E.Ī fully automated iterative design method has been developed by which an airfoil with a substantial amount of natural laminar flow can be designed, while maintaining other aerodynamic and geometric constraints. A Method for the Constrained Design of Natural Laminar Flow Airfoils
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