航空飞行器之气动力最佳化设计.pptVIP

Start at a point P. Compute F(x,y) at P Take a small step to the right, find F(x+Dx, y) Use this to find ?F/ ?x at P. Similarly find ?F/ ?y at P Construct a gradient vector . Find new values of x,y ● Pseudo-code of the Intelligent GA ? Procedure: The Genetic Algorithm Begin create initial population randomly; do { choose a pair of parents from population; /* REPRODUCTION */ children=Intelligent CROSSOVER(parent1, parent2); /* Taguchi’s Orthogonal Arrays */ MUTATION(children); } while (stopping criterion not satisfied); End; ● A Multi-Modal Function Riccati Equation: ● A Nonlinear Dynamic Control Function with Large Parameter Optimization Problem (LPOP) ● Airfoil Fitting CFD Aero Analysis Baseline Airfoil Configuration New Design Variables Objective Constraints Shape Modes Combination Define Shape Functions Optimizer Process Sensitivity Analysis Program Start Program Stop Optimum Minimum Obj. @ Constraints Yes No New Airfoil Configuration Grid Generation ● Flow Chart of Optimization Procedure (1) High Lift Airfoil Design (I) VI. Results and Discussions ● Mach Number Contours of Flow Field ● The Geometry Plots of Airfoil Shape ● The Comparison of Pressure Distributions (2) High Lift Airfoil Design (II) * * 航空飛行器之氣動力最佳化設計 現職：立德管理學院資訊管理學系副教授兼系主任 (91.8~迄今) .tw/ 歷任：永達技術學院機械系副教授(89.8~91.7) 中山科學研究院航空研究所簡聘技正暨副研究員 (80.10~89.8) 劉振隆 Aircraft Design Airfoil Section Design Wing Planform Design Fuselage Design Optimization Algorithms Results and Discussions VII. Conclusions CONTENTS (1) Design Parameters of an Aircraft I. Aircraft Design ● Preliminary Configuration Definition ● Experimental Data (Wind Tunnel) Based ● 78 Combinations of Variables ─Wing Planform ─Airfoil Section (Fixed and Variable) ─Wing-Body Relationship ─Inlet Location and Type ─Single vs. Twin Vertical Tail ─Forebody Strakes (2) Configuration Evol