Supersonic Flow in the Corner Formed by Two Intersecting Wedges

Theme E12 for over a decade, have investigated the supersonic flowfield in the axial corner formed by two intersecting wedges. The understanding and prediction of this type of interference flow is of considerable interest to the designer of high-performance hypersonic aircraft and spacecraft (Space Shuttle Orbiter) because of the high local heating that occurs in this region. Such flows are encountered, for example, at wing-body junctures, at control surface roots, and within supersonic inlets. Theoretical attempts at modeling the corner flow problem have been made in the past,' but these employed simplifying or incorrect assumptions and thus resulted in questionable solutions. According to the recent survey paper of Korkegi, there exists no adequate method of predicting even the inviscid flow structure. In the present paper, a numerical solution for the inviscid corner flow is computed using a second-order accurate shock-capturing technique.