Numerical Analysis of Supersonic Flow and Shockwave Behavior Over a Convex Wedge

Abstract

The present study describes the flow behavior around the leading edge of a convex wedge having a specific dimension under varying upstream Mach numbers ranging from 1.4 to 2. The interaction between the free stream flow and the wedge significantly affects flow parameters such as static pressure, density, static temperature, downstream Mach number, and shock standoff distance (SSD), which are crucial for efficient aerodynamic design. Previously, various researchers have considered the convex wedge flow configuration specifically for inviscid flow but limited attention has been given to the detailed behavior of flow parameters at the leading edge of a convex wedge under varying upstream Mach numbers. The results indicate that, static pressure increased almost 80% at upstream Mach number 2 at the leading edge of the convex wedge. Density, static temperature, downstream Mach number all of them increased by 40%, 28%, and 40% respectively. The downstream Mach number, at first increases slowly but change takes place rather rapidly when the upstream Mach number crosses the value of 1.6. Again, the SSD showed an abrupt change (almost 95% decrease of its initial value at upstream Mach number 2).  The leading edge was chosen for this study since it’s considered to be the critical design point which experiences the highest thermal and aerodynamic loads due to the shockwave. Evaluating flow behavior at this point is crucial in managing shockwave-induced loads.