Calculation of hinge moment of 3-D aileron

The flows around 2-D and 3-D wings with ailerons deflected are numerical simulated in cases of subsonic, transonic and supersonic speeds. The Navier-Stokes equations are solved using finite volume method and AUSM+ scheme, and the four-step Range-Kutta method for time marching. Turbulence models used are Baldwin-Lomax and Spalart-Allmaras models. The 2-D calculated pressure results coincide well with the experiment data and computational fluid dynamics (CFD) software simulation results. Using mismatched multiblock grids, the flow fields of 3-D wing with different aileron deflected angles and gaps are simulated at different Mach numbers, angles of attack and Reynolds numbers. The calculated hinge moment values of control surfaces are compared with the experiment data. It is shown that the presented numerical method is reliable and can be used as an effective tool for analyzing such kind of complex flow. The reverse varying trend of the hinge moment with angle of attack in subsonic incoming flow is observed and investigated. The effects of Reynolds number and aileron gap are analyzed primarily.