Abstract:

The flow over delta wing with 65° and 70° swept at high angle of attack is investigated by solving the three dimensional, compressible Navier Stokes equations utilizing the second order upwind TVD algorithm(Harten Yee).The calculated results indicate that the choice of the limiter function in TVD scheme has an important influence on the numerical simulation which is carried out on the delta wing flow structure. The development of vortex is studied with ZHANG Han xin's vortex analysis theory. In addition, the second vortex breakdown performance and the grid influence are discussed in this article.

Key words: delta w ing, separat ion flow, numericalmethod, lim it cycle