Numerical Studies Of Aircraft Static Aeroelastisity Based On N-S Equations

In the present thesis, the traditional horse shoe vortex lattice method and the CFD method based on Navier-Stokes equations to numerically simulate the aerodynamic force of the elastic wings. Then the flexibility method is used to develop the method of calculating the static dynamic features of the wings of aircrafts under aerodynamic force.The vortex lattice method is a practical numerical calculation method in the lift force area theory. Its calculation model is horse shoe vortexes distributed not only along the wingspan direction but also along the wing chord direction. The whole wing is represented by limited discrete vortex systems. The induced speed of the control point is induced by the attached vortex and the left and right free vortexes.In regard to grid generation technology, algebraic approach and local part deformation technology are developed to generate 3 dimensional grid which sticks to the aircraft. And a quick elastic deformation technology is developed to generate the grid after the deformation.The finite-volume method based on Roe scheme is applied to solve the three-dimensional N-S equations, and the five-stage Runge-Kutta explicit scheme is used for time marching. Spalat-Allmaras One-Equation turbulence model is employed to the simulations of turbulent flows. Local time-stepping, enthalpy damping and implicit residual smoothing are applied to accelerate the solution for stationary problems.Basing on the horse shoe vortex lattice method and the Navier-Stokes equations, the flexibility method is developed to calculate the aerodynamic features of the aircraft wings when static areoelasticity is considered, and the results are compared with those that are calculated using the mode method. Computational results are valued pratically.