Ice Wing Adaptive Unstructured Grid Generation And Flow Field Analysis

The accumulation of ice on aircraft components, such as wings, engine intakes, occurs when the aircraft flies. The present of ice accretion on unprotected aircraft components can greatly reduce lift, increase drag, make control surfaces fail, and so on. Ice accretion of aircraft has been a major concern to flight safety, and the study of ice accretion is absolutely necessary.Firstly in this paper, the two-dimension model of the icing airfoil was gained by simulating the growth of ice of the simplified model at different freezing conditions while the boundary function was added. Then use the NURBS curve to simplify the model with experiment data. At last build the three-dimension model with two-dimension models by using the Level set method. A speed function with feeding back theory was given to modify the change on different cut piece of the ice. So that a kind of three-dimension ice model with non-periodic change could be found.Mesh generating is an important part of CFD research as well as an important field in numerical analysis and calculation. Numerical method is an effective numerical analyzing method developing depend on computer. Generating adaptive mesh which could show the structure and the sharp is necessary to the application of adaptive finite element method. The generation algorithm of unstructured mesh in three-dimension and the adaptive mesh algorithm was studied in this paper and generated the unstructured mesh of icing wing by programming.In real flow field especially in the supersonic flow field, complicated wave structure and different space-time metric always appears. And the numerical simulation result could be affected greatly by these metrics. Most directly, smallest mesh element volume can be taken to match all the metrics. But it would be a great number of mesh elements and short time step which may take long time to calculate and lager room to store the date. This problem may be figured out by the adaptive method. In this paper, unstructured mesh adaption of icing wing base on model sharp was done by adding a space control function and the quasi-optimal tetrahedron algorithm. The mesh was satisfied to the numerical simulation research of the icing wing.At last in this paper, the flow field calculation of icing wing was compared with the clean one based on Euler equation. The results indicated that ice had adverse impact on aerodynamic.