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战斗机类小展弦比薄机翼的气动设计,主要考虑机翼的平面形状以及弯扭和厚度修形设计,忽略了机翼翼型的精细化设计,因此气动分析手段一般采用Euler方程结合黏性阻力修正的方法.以某典型战斗机机翼为例,分别使用Euler和RANS方程对机翼的流场与气动特性进行了数值模拟,发现Euler方程无法精确捕捉附面层内的流场结构,证明传统使用的Euler方程已不能满足战斗机机翼精细化设计的需要.对该机翼的翼型进行了气动优化设计,发现翼型的设计对该小展弦比薄机翼会失效,证明这类机翼必须在三维环境下进行多剖面翼型设计.综合FFD参数化方法、稳健的动网格技术、Kriging代理模型和粒子群算法,构建了三维气动优化设计方法.利用该方法对该机翼三个剖面翼型进行了跨音速巡航状态单目标以及跨音速/超音速巡航状态多目标精细化化设计,优化设计后机翼的气动性能得到很大的提高.
Fighter small aspect ratio thin wing aerodynamic design, the main consideration of the wing shape and bending and thickness modification design, ignoring the wing wing of the refined design, aerodynamic analysis methods generally use the Euler equation with viscosity Resistance modification method.With a typical fighter wing as an example, Euler and RANS equations were used to simulate the flow field and aerodynamic characteristics of the wing respectively, and found that the Euler equation can not accurately capture the flow field structure in the attached layer, The traditional Euler equation can not meet the needs of fighter wing design.The aerodynamic design of the airfoil has been done and it is found that the design of the airfoil will not work for this small aspect ratio thin wing, The airfoil must be designed with multi-profile airfoil in three-dimensional environment.A three-dimensional aerodynamic optimization design method is constructed based on FFD parameterization method, robust dynamic grid technique, Kriging agent model and particle swarm optimization algorithm.Using this method, Three profiles of airfoils were transonic cruise single target and transonic / supersonic cruise multi-target refinement design, the aerodynamic performance of the optimized wing Get a big improvement.