21st Congress of International Council of the Aeronautical Sciences, Melbourne, Australia, 13-18 September, 1998
Paper ICAS-98-7.4.2


CONICAL EULER EQUATIONS' SOLUTION BASED ON THE UNSTRUCTURED GRID AND ITS APPLICATION TO A VORTICAL FLOW OVER A HIGHLY SWEPT DELTA WING

Yao P. -H., Morishita E.
University of Tokyo, Japan

Keywords: conical euler equations' solution, unstructured grid, vortical flow, highly swept delta wing

The supersonic flow over highly swept delta wings was analyzed by using conical flow equations. Numerical solutions for Euler equations were obtained by introducing the artificial damping terms to suppress the numerical oscillations due to shock waves. The authors attempted to develop the conical Navier-Stokes equations whose viscous terms were modified as in the conical Euler equations in order to replace the artificial damping terms. First, preliminary numerical studies were done based on simple rectangular grids by utilizing the spreadsheet cells and their iteration functions instead of depending on the computer programs. An unstructured example is also being analyzed. The numerical results were compared to the supersonic experimental data of swept delta wings with subsonic and supersonic leading edges.


view full paper