Drag Reduction Technology And Static Aeroelastic Influence Analysis Of Bump Installed On The Wing

In recent years, civil aircraft increases the drag-divergence Mach number by using supercritical wing, but it can't eliminate the generation of shock wave anyway. As a shock control technique, the bump is installed on the upper surface to compress the airflow locally so that the strength of the shock wave is weakened and the drag reduction is realized by changing the local shape of the airfoil and the wing.In this paper, we use the evolutionary strategy algorithm of the Isight optimization software to establish a bump optimization design platform by integrating the bump shape generator program and grid generation software Gridgen and flow field simulation software Fluent. Through this platform,the drag reduction characteristics of the supercritical airfoil and wing are numerical studied. The results show that the airfoil with optimized two-dimensional bump has a good effect on drag reduction,although it can't change the downtrend of the lift-drag characteristics, it improves a lot when compared with the clean airfoil, and the flow separation phenomenon has been delayed or even suppressed; The three-dimensional bump has spanwise characteristics, which is not only suitable for the straight wing but also for the swept wing, the wing with optimized three-dimensional bump can improve the flow of the flow direction and reduce the drag of the wing, but at the same time it also has influence on the spanwise flow. The change of the Mach number and the angle of attack have bigger impact on the bump height and the location of the bump while have smaller impact on the bump length and the position of the bump crest, the bump length always gets the maximum value, the position of bump crest is located near the center of the bump. The width of bump is not sensitive to the flow. The platform is versatile and the optimization process is automatic, the result is reliable.In this paper, we use the flexibility method and iterative method to study the influence of static aeroelasticity by the bump, the results show that the preliminary design of the three-dimensional bump has little effect on the static deformation; the bump still has the effect of drag reduction on the wing with static deformation.