摘要
针对某民机起飞、巡航、着陆三种典型飞行状态,通过CFD方法研究翼梢小翼后掠角变化对该机不同状态下气动性能的影响。仿真结果表明,在起飞、巡航、降落三种不同状态下,随着翼稍小翼后掠角的增大,升阻比的变化都呈现先升高后下降的趋势;同时得出在以10°为步长的计算条件下,以升阻比为考核指标,对应各飞行状态的最佳后掠角分别为30°、50°、40°。该结论对今后变体翼梢小翼的研究有一定的参考价值。
The effects of winglet＇s sweepback angle on civilian airplane＇s aerodynamic performance at three differ- ent flight conditions, taking-off, cruising and landing, are studied with using CFD method. The result shows that for the simplified airfoil in this paper, the regular pattern of lift-to-drag is first increased then decreased with the increase of winglet sweepback angle in all the three different flight conditions. And it also abtained that the best sweepback angles in the three flight conditions, taking-off, cruising and landing, are 30°, 50°, 40°, in a 10°- step calculation condition. The conclusion has certain reference value to the study of the variable winglet in the fu- ture.
出处
《民用飞机设计与研究》
2014年第1期48-51,共4页
Civil Aircraft Design & Research
关键词
翼梢小翼
后掠角
迎角
气动性能
升阻比
Winglet
Sweepback Angle
Attack Angle
Aerodynamic Performance
Lift-to-drag Ratio
