Optimization for Airfoil Design

نویسندگان

  • Robert Carrese
  • Xiaodong Li
چکیده

A significant challenge to the application of evolutionary multiobjective optimization (EMO) for transonic airfoil design is the often excessive number of computational fluid dynamic (CFD) simulations required to ensure convergence. In this study, a multiobjective particle swarm optimization (MOPSO) framework is introduced, which incorporates designer preferences to provide further guidance in the search. A reference point is projected onto the Pareto landscape by the designer to guide the swarm towards solutions of interest. The framework is applied to a typical transonic airfoil design scenario for robust aerodynamic performance. Timeadaptive Kriging models are constructed based on a high-fidelity Reynolds-averaged Navier– Stokes (RANS) solver to assess the performance of the solutions. The successful integration of these design tools is facilitated through the reference point, which ensures that the swarm does not deviate from the preferred search trajectory. A comprehensive discussion on the proposed optimization framework is provided, highlighting its viability for the intended design application. 67.1 Airfoil Design....................................... 1311 67.1.1 Airfoil Design Architecture .......... 1311 67.1.2 Intelligent Optimization: PSO ...... 1312 67.1.3 Multiobjective Optimization ....... 1313 67.1.4 Surrogate Modeling ................... 1316 67.2 Shape Parameterization and Flow Solver ................................... 1317 67.2.1 The PARSEC Parameterization Method .................................... 1317 67.2.2 Transonic Flow Solver................. 1318 67.3 Optimization Algorithm........................ 1319 67.3.1 The Reference Point Method ....... 1319 67.3.2 User-Preference Multiobjective PSO: UPMOPSO ........................... 1320 67.3.3 Kriging Modeling ....................... 1322 67.3.4 Reference Point Screening Criterion ................................... 1323 67.4 Case Study: Airfoil Shape Optimization . . 1323 67.4.1 Pre-Optimization and Variable Screening .............. 1324 67.4.2 Optimization Results.................. 1325 67.4.3 Post-Optimization and Trade-Off Visualization ........ 1326 67.4.4 Final Designs ............................ 1327 67.5 Conclusion........................................... 1329 References ................................................... 1329

برای دانلود متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

ثبت نام

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

Airfoil Shape Optimization with Adaptive Mutation Genetic Algorithm

An efficient method for scattering Genetic Algorithm (GA) individuals in the design space is proposed to accelerate airfoil shape optimization. The method used here is based on the variation of the mutation rate for each gene of the chromosomes by taking feedback from the current population. An adaptive method for airfoil shape parameterization is also applied and its impact on the optimum desi...

متن کامل

Applying evolutionary optimization on the airfoil design

In this paper, lift and drag coefficients were numerically investigated using NUMECA software in a set of 4-digit NACA airfoils. Two metamodels based on the evolved group method of data handling (GMDH) type neural networks were then obtained for modeling both lift coefficient (CL) and drag coefficient (CD) with respect to the geometrical design parameters. After using such obtained polynomial n...

متن کامل

The Effects of Shape Parameterization on the Efficiency of Evolutionary Design Optimization for Viscous Transonic Airfoils

The effect of airfoil shape parameterization on optimum design and its influence on the convergence of the evolutionary optimization process is presented. Three popular airfoil parametric methods including PARSEC, Sobieczky and B-Spline (Bezier curve) are studied and their efficiency and results are compared with those of a new method. The new method takes into consideration the characteristics...

متن کامل

Airfoil Design Optimization for Airplane for Mars Exploration

Aerodynamic design optimization of an airfoil for the Mars exploration airplane has been demonstrated by using an evolutionary algorithm. The adaptive range genetic algorithm is used for efficient and robust design optimization. Two-dimensional Navier-Stokes solver is used for accurate aerodynamic performance evaluation. The present computation is parallelized on the SX-6 vector computers in In...

متن کامل

Transonic Airfoil Shape Optimization in Preliminary Design Environment

A modified profile optimization method using a smoothest shape modification strategy (POSSEM) is developed for airfoil shape optimization in a preliminary design environment. POSSEM is formulated to overcome two technical difficulties frequently encountered when conducting multipoint airfoil optimization within a high-resolution design space: the generation of undesirable optimal airfoil shapes...

متن کامل

A Study on Airfoil Design for Future Mars Airplane

An optimum airfoil design for future Mars airplane for Mars exploration is obtained by evolutionary computation coupled with a two-dimensional Reynolds-averaged Navier-Stokes solver. The optimized airfoil design is also compared with other airfoil designs optimized at different Reynolds number or at different Mach number to discuss Reynolds number and Mach number effects on airfoil design. Thes...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

برای دانلود متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

ثبت نام

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

عنوان ژورنال:

دوره   شماره 

صفحات  -

تاریخ انتشار 2015