学术论文

      高效低噪的二维翼型优化设计

      A numerical optimization for high efficiency and low noise airfoils

      摘要:
      针对传统的气动优化设计未考虑气动噪声影响的局限性,开展了基于噪声预测模型的气动优化设计方法在二维翼型中的应用研究。建立了由几何外形参数化方法、径向基函数(Radial Basis Function,RBF)动网格技术、改进粒子群优化算法、气动分析方法、气动噪声预测方法等五大模块构成的优化设计系统,且各模块均采用标模算例进行验证。通过对二维 SC(2)-0714超临界翼型进行了单点多目标优化设计。通过对比翼型几何形状、压力系数分布以及在不同迎角下的气动力系数曲线与总声压级的关系可得,翼型头部半径、厚度影响其头部压力峰值、压力恢复、逆压梯度等特性,从而影响升阻比和总声压级,逆压梯度越小,翼型的总声压级越小。优化结果表明,在设计状态下显著提高了升阻比、降低气动噪声,考虑气动噪声的二维翼型优化设计系统可在实际的工程设计中进行应用。
      Abstract:
      In view of the traditional aerodynamic optimization design without considering the effects of aerodynamic noise,the aerodynamic optimization design method based on noise prediction model was studied in the application of two-dimensional airfoil.The free deformation parametric method,radial basis function (RBF)mesh deformation technology, improved particle swarm optimization algorithm,pneumatic analysis method,and the aerodynamic noise prediction method for the optimization design,the five modules were established and formed a system.Finally,a single-point multi-objective optimization design of two-dimensional supercritical airfoil SC(2)-0714 was carried out.The effect of different airfoils geometry,pressure coefficient distribution,as well as the relationship between the aerodynamic coefficients and overall sound pressure level under different angles of attack were studied.The analysis showed that airfoil geometry could affect its head peak pressure,pressure recovery,adverse pressure gradient and other characteristics,which could change the lift-drag ratio and overall sound pressure level (SPL).And the adverse pressure gradient was closely related to overall SPL. Optimization results show that under the design condition the design system can significantly improve the lift-to-drag ratio, reduce the aerodynamic noise.It thus can be applied in practical engineering design.
      作者: 李鑫 [1] 屈转利 [1] 李耿 [1] 刘雨 [1] 李国才 [1] 余培汛 [2]
      Author: LI Xin [1] QU Zhuanli [1] LI Geng [1] LIU Yu [1] LI Guocai [1] YU Peixun [2]
      作者单位: 中国航天科技集团公司第四研究院第四十一所,西安,710025 西北工业大学 航空学院,西安,710072
      刊 名: 振动与冲击 ISTICEIPKU
      年,卷(期): 2017, 36(4)
      分类号: V211.3 V211.4
      在线出版日期: 2017年3月20日