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针对后缘连续变弯度对跨声速翼型气动特性的影响进行了研究。首先不考虑翼型后缘连续变弯度,基于搭建的优化设计系统对跨声速翼型进行气动减阻优化设计,通过添加不同的约束优化得到两种跨声速翼型:无激波翼型和超临界翼型。然后在这两种翼型的基础上,以后缘偏转角度为设计变量、以阻力系数最小为目标,针对不同的升力系数分别进行优化设计,并根据优化结果深入分析后缘连续变弯度对这两种翼型极曲线特性的影响机理。优化结果表明:无激波翼型与超临界翼型相比,其设计点处的气动特性较好,但鲁棒性较差;升力系数小于设计升力系数时,应用后缘连续变弯度后,无激波翼型的极曲线特性明显提高,减阻最高达到3.9%,而超临界翼型的极曲线特性提高不明显;升力系数大于设计升力系数时,应用后缘连续变弯度后,无激波翼型和超临界翼型的极曲线特性都明显提高,减阻分别达到2.4%~18.1%和1.7%~13.2%。
The effect of continuous turning on the trailing edge on aerodynamic characteristics of transonic airfoils was studied. Firstly, without consideration of the continuous curvature of the trailing edge of the airfoil, the optimization design of the transonic airfoil was optimized by aerodynamic drag reduction based on the optimized design system. Two kinds of transonic airfoils were obtained by adding different constraints: Critical airfoil. Then based on the two airfoils, taking the angle of trailing edge as the design variable and the target of the drag coefficient as the minimum, the optimal design for different lift coefficient is carried out respectively. Based on the optimization results, Influencing mechanism of airfoil polar curve. The optimization results show that the non-shock airfoil has better aerodynamic characteristics than the supercritical airfoil but poor robustness. When the lift coefficient is less than the design lift coefficient, The characteristics of the non-shock airfoil with polar curve are obviously improved, with the maximum drag reduction of 3.9%, while the supercritical airfoil has no obvious increase of the polar curve. When the lift coefficient is greater than the design lift coefficient, The polar curve characteristics of both the airfoil and the supercritical airfoil are obviously improved, with the drag reduction reaching 2.4% ~ 18.1% and 1.7% ~ 13.2% respectively.