Multi-objective optimization of propeller airfoil for general aviation aircraft
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摘要:
为获得具有较高气动性能、较低气动噪声的翼型，对某通用飞机螺旋桨所用RAF-6翼型进行优化设计。首先，使用CFD/FW-H（Ffowcs Williams-Hawkings）方法对翼型进行了流场与声场数值仿真计算；其次，分别研究翼型最大厚度、最大厚度位置、后缘下弯角度与后缘下弯位置4个设计变量对其气动性能与气动噪声的影响规律；进而，以巡航状态为设计点，以高升阻比及低气动噪声为优化目标对翼型进行多目标优化设计，获得Pareto解集；最后，通过试验验证翼型优化后的螺旋桨拉力提高14.7%，气动噪声降低2.3 dB。
Abstract:In order to obtain an airfoil with higher aerodynamic performance and lower aerodynamic noise, the RAF-6 airfoil for a general aviation aircraft propeller was optimized. The flow field and sound field of the airfoil were simulated by CFD/FW-H method. The influence laws of four design variables, i.e. the maximum thickness, the position of the maximum thickness, the downbending angle and position of trailing edge, on its aerodynamic performance and aerodynamic noise were studied respectively. Taking the cruise state as the design point, the airfoil multi-objective optimization design was carried out with higher lift-drag ratio and lower aerodynamic noise as the optimization objectives, and the Pareto solution set was obtained. The experimental results verified that the optimized airfoil increased the propeller thrust by 14.7% and reduced the aerodynamic noise by 2.3 dB.
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Key words:
- airfoil /
- aerodynamic performance /
- aerodynamic noise /
- multi-objective optimization /
- NSGA-Ⅱ algorithm
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图 6 不同最大厚度翼型的气动特性
Figure 6. Aerodynamic characteristics of airfoil with different maximum thicknesses
图 7 不同最大厚度翼型的气动噪声
Figure 7. Aerodynamic noise of airfoil with different maximum thicknesses
图 8 不同最大厚度位置翼型的气动特性
Figure 8. Aerodynamic characteristics of airfoil with different maximum thickness positions
图 9 不同最大厚度位置翼型的气动噪声
Figure 9. Aerodynamic noise of airfoil with different maximum thickness positions
图 10 不同后缘下弯角度翼型的气动特性
Figure 10. Aerodynamic characteristics of airfoil with different trailing-edge downbend angles
图 11 不同后缘下弯角度翼型的气动噪声
Figure 11. Aerodynamic noise of airfoil with different trailing-edge downbend angles
图 12 不同后缘下弯位置翼型的气动特性
Figure 12. Aerodynamic characteristics of airfoils with different trailing-edge downbend positions
图 13 不同后缘下弯位置翼型的气动噪声
Figure 13. Aerodynamic noise of airfoils with different trailing-edge downbend positions
图 17 优化前后翼型气动特性对比
Figure 17. Comparison of aerodynamic characteristics of airfoil before and after optimization
图 18 优化前后翼型气动噪声对比
Figure 18. Comparison of aerodynamic noise of airfoil before and after optimization
图 19 各攻角下噪声声压级对比
Figure 19. Comparison of sound pressure level at different angles of attack
表 1 优化结果
Table 1. Optimization results
参数 基准翼型 优化翼型 增量 升力系数 0.824 0.889 +7.89% 阻力系数 0.0168 0.0165 −1.79% 升阻比 48.92 53.91 +10.2% 声压级/dB 132.933 131.332 −1.6 
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表 2 螺旋桨优化前后结果对比
Table 2. Comparison of result of propeller before and after optimization
参数 基准螺旋桨 优化螺旋桨 试验值 计算值 试验值 计算值 拉力/N 327.74 330.53 375.92 380.36 效率/% 78 80.5 79 81.6 声压级/dB 87.87 86.32 85.57 84.74
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