A Numerical Stimulation On Flow Control Of The Wing Surface With The Adoption Of The Spoiler

The aerodynamic characteristics of flight vehicle flying at high angle of attack are extremely complicated. For example, the pitching moment, yawing moment and the yawing force caused by asymmetric fractionation of the flow around the fore body, the unsteady aerodynamic force of the aircraft and the nonlinearity will bring many difficulties and challenges to the flight control and safety. When the aircraft flying at the high angle of attack, there is separation phenomenon above the aerofoil, which is likely to lead the deterioration of the aerodynamic characteristics of the aircraft. An effective method of overcoming the adverse effect is to mange to change its separation characteristic through active control and passive control. Spoiler is an aerodynamic device that can achieve above requirements. Therefore, it’s very necessary to study the problem of the spoiler’s flow from the angle of practical value.The paper reviews about the domestic and international analysis of the unsteady flow of the spoiler, and introduces the application of spoiler in the field of aircraft, missile and engineering practice. And base on this, numerical value calculation of the influence of spoiler of different angels on the airfoil aerodynamic characteristics is presented.First of all, the paper performs numerical simulations of the flow field of the aircraft wings in the absence of spoiler and gets the results of simulation of different angles of attack and critical angle of attack. Then the spoiler is installed, and numerical stimulations of aircraft wings are performed by changing the angle of spoiler. At last, the paper draws a conclusion that the state of the lee area vortex can be controlled by installing spoiler on the aircraft wings. The main vortex formed in the leeside of the spoiler is the primary cause for generating lift; trailing vortex effects main vortex and it’s the reason of reducing lift. Therefore, the method of increasing the spoiler’s angle in a certain range can be used to enhance drag and reduce lift, thus the aircraft can be controlled to make an effective pneumatic brake.