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1、上海交通大學碩士學位論文圖索引圖索引圖2-1以二維函數(shù)為例表示出變異向量的生成.....................................................11圖2-2試驗向量的生成.............................................................................................11圖2-3簡單差分進化算法運算流程.........................................................................12

2、圖2-4Pareto最優(yōu)邊界..............................................................................................22圖3-1任意六面控制體單元.....................................................................................26圖3-2用外插公式計算物而壓強..................................................................

3、...........32圖4-1RAE2822計算網(wǎng)格（O型）.........................................................................45圖4-2RAE2822的計算結果與實驗結果對比.........................................................46圖4-3RAE2822計算壓力等值線.............................................................................46圖4-4R

4、AE2822計算等馬赫數(shù)線.............................................................................47圖4-5目標翼型與基準翼型幾何外形對比.............................................................48圖4-6目標翼型與基準翼型壓力分布對比.............................................................48圖4-7基準翼型和優(yōu)化翼型的幾何外形對比...............

5、..........................................49圖4-8基準翼型與優(yōu)化翼型的壓力分布對比.........................................................50圖4-9升力系數(shù)與阻力系數(shù)的下降趨勢.................................................................52圖5-1機翼參數(shù)化模型........................................................................

6、.....................54圖5-2并行計算流程.................................................................................................60圖5-3ONERAM6機翼網(wǎng)格（C-H型）.................................................................61圖5-4機翼上、下表面的壓力等值線......................................................

7、...............62圖5-5ONERAM6機翼各剖面壓力分布計算結果與實驗結果對比.....................62圖5-6基準機翼與優(yōu)化機翼的幾何外形變化對比.................................................64圖5-7基準機翼上、下翼面壓力等值線.................................................................65圖5-8基準機翼沿展向20%，44%，65%和90