Dynamic Calculation Of Complex Flow Field Unsteady Aerodynamic And Aeroelastic Research

The research of this dissertation is focused on how to simulate numerically the steady and unsteady subsonic, transonic and supersonic viscous flows around wing and aircraft by computational fluid dynamics method. On this basis, several kinds of aeroelastic problems of aircraft are investigated. Finally for all the above aeroelastic problems, distributed parallel computation is accomplished.The body-Fitted viscous moving mesh for unsteady flow is generated by algebraic finite integration. Then the steady and unsteady subsonic, transonic and supersonic viscous flows around airfoil and some aircraft are numerically simulated. The 3-dimensional unsteady Navier-Stokes equations are solved using the implicit LU-NND algorithm, with Baldwin-Lomax turbulent model. On the basis of simulating unsteady viscous flow, coupling the structure dynamics equations, the problems of static aeroelasticity and flutter are investigated for wings and elevator. Basing on the static aeroelasticity, the jig-shape and the attack angle design have been studied.Generally, much computing time is needed in unsteady flow computation. In order to reduce the computing time and improve efficiency, the procedure has been paralleled and the distributed parallel computation is accomplished in a net with four PCs. The parallel computation of static aeroelasticity and flutter has been initiated at home.On this basis, the work includes four parts. Firstly, many examples, simulating the steady and unsteady viscous flows around several wings and some aircraft, are given in this paper. Secondly, the static aeroelastic problems and jig-shape design, as a kind of Multi-disciplinary Design Optimization (MDO), are investigated for sweep wing and super-critical wing. Numerical results are in good agreement with otherreference data. The method and the program presented in this paper are verified. Thirdly, the subsonic, transonic and supersonic flutter critical speed of wings and aircraft is numerically simulated. Some numerical results are in good agreement with experimental data. Fourthly, the numerical results and computing speed of the series program and the parallel program are compared in this paper. It indicates the feasibility and the efficiency of the distributed parallel computation in solving complicated unsteady flows. That means, as a good numerical method, distributed parallel computation can improve computing speed greatly in the same accuracy.