Pressure Distribution Analysis for Aerodynamic Characterization Across Varying Flight Regimes

Understanding the pressure distribution of flight vehicles across varying Mach regimes is critical for high-speed aerodynamic applications. This study aims to characterize and compare analytical methods used to estimate the pressure coefficient distributions across subsonic, supersonic, and hypersonic flight regimes. Methods include but are not limited to the panel method for subsonic flight, compressible flow equations for supersonic flight, and Newton’s method for hypersonic flight. These analytical techniques are implemented in MATLAB and validated against computational fluid dynamics (CFD) simulations using Ansys Fluent as well as published experimental wind tunnel data. To allow for comparison across all flight regimes, a consistent slender wedge geometry is analyzed for each method. Deviations of each analytical method are compared, providing insights into their applicability in aerodynamic design. The results provide a basis for selecting appropriate analytical methods in preliminary vehicle design, developing the understanding of theoretical models and their limitations.