Numerical analysis of supersonic flow past a delta-wing

Abstract

Three-dimensional inviscid supersonic flow past the compression side of a delta wing with an angle of attack has been numerically solved using a Russian-developed BVLR method. The delta wing considered in this report are of two type of configuration : a flat plate delta wing with curvilinear leading edge, and a delta wing of straight leading edge having streamwise lenticular crosssection and spanwise double wedge crosssection. The flow properties on an initial plane, which are needed to initiate the flow calculation, have been determined with substantial accuracy through an iterative procedure which make use of the fact that airfoil geometry becomes simplified near the vertex of delta wing. The pressure curves and shock profiles have been determined for varing freestream Mach number, sweep-back angle, thickness ratio and angle of attack. Comparision with other literature has been made for the case of the flat-plate delta wing which has straight leading edge and for the case of a double-wedge delta wing having constant streamwise slope. The agreement has turned out very good.