Numerical Simulation of 2D Wedge to Determine Pitching Moment Derivative and Shock Behaviour at Hypersonic Mach Numbers

Abstract

Creating a numerical model for the 2D wedge flow field is the aim of this study. Wedge shapes are frequently used in defensive applications as stabilising surfaces for hypersonic projectiles like rockets, missiles and aircraft. Delta or wedge-shaped wings are frequently employed as the main wing on hypersonic aircraft and weapons to maintain stability. Examining the static pressure, derivative of the pitching moment at different wedge pivot points and shock behaviour for the nose of a wedge-shaped plane or missile at various Mach numbers and incidence angles in the hypersonic zone is the primary objective of the current study. A detailed investigation was conducted on the numerical simulation findings. The fluctuation of the pitching moment derivative is influenced by the Mach number, angle of attack (α) and wedge angle (θ), as demonstrated by the application of computational fluid dynamics (CFD) analysis to estimate the pitching moment derivative (Cmq). Similarly, CFD analysis is used to quantify static pressure, showing that the Mach number influences the (Cmq) variation (α) and (θ). Static pressure increases with increasing Mach number (α) and (θ). Moreover, at hypersonic Mach numbers, the shock angle decreases as the Mach number increases. The vehicle accelerates at a Mach number of 15.5, reaching hypersonic Mach because the shock is at the surface and moves away from the nose as the Mach number rises.