The Characteristic Research Of Lift Enhancement And Drag Reduction On Aircraft

The wing assumed aircraft lift and a certain percentage of the resistance, which is one of themost important components in the aircraft, so the wing aerodynamic optimization is extremelyimportant in order to achieve the goal of lift drag reduction. Airliner wing lift to improve resistancedecrease means that the aircraft will save more fuel for airlines, thereby reducing the cost of themission to improve the economics of the flight.Firstly as a model to633418straight wing, wingtip vortex generated by experimental methods,development and dissipation mechanisms. Experimental results show that at the total pressure of thewing tip vortex core is less than the free-stream, the total pressure coefficient greater loss,Experiments also found that the formation of the tip vortex was originally developed by two of thedevice on the wing tip of the no wingtip shares of small vortex aggregation, these two small vortexone form wingtip on the surface, one formed in the wing lower surface, both convergence in the closeposition of the trailing edge, which is the prototype of the wingtip vortex. The wingtip vortex on thewing did not stall the increased random wing angle of attack increases, enhanced, when the stall of thewing, the wingtip vortex suddenly disappeared, rupture turbulence.The winglet is a common wing lift drag reduction device, its not only the purpose of lift dragreduction can be achieved, but also to abate the wing tip vortices generated. Installation angle of thewinglets, this paper designed a movable rudder winglets and rudder deflection can be approximated tochange the purpose of winglets installation angle. The experiment found that the winglets can thepartial turn the wheel surface can change the aerodynamic characteristics of the wing, for differentaircraft flight status, such as the aircraft’s take-off, cruise and landing, appropriate changes wingletswing deflection angle can improve lift, to achieve the purpose of lift drag reduction.Finally, the larger angle of attack for the wing upper surface flow separation, this article NACA0015airfoil based on the design and manufacture of a leading edge of the lower surface of the jetwing forward. The experiments show that, under the wing surface of the leading edge of the forwardjet can be effective to improve the aerodynamic characteristics of the wing, which not only can bewell controlled wing greater angle of attack when the upper surface of the flow separation, but alsoeffectively increase the maximum lift of the wing coefficient and stall angle of attack. The experimentalso proved, the jet not need to have been continuous, intermittent jet control. The lower surface of thewing leading edge forward jet method also has the advantages of low power consumption, highefficiency, and to a certain value of engineering applications.