This tool facilitates the computation of flow properties associated with the expansion of a compressible fluid around a sharp corner. It allows users to determine parameters such as Mach number, pressure, and temperature after an isentropic expansion, given the initial flow conditions and the turning angle. For example, knowing the upstream Mach number and the angle through which the flow turns, the calculator can precisely predict the downstream Mach number and corresponding pressure ratio.
The utility of this calculation stems from its application in supersonic aerodynamics, particularly in the design of aircraft wings, nozzles, and other aerodynamic surfaces. Accurate prediction of flow behavior during expansion is critical for optimizing performance and minimizing drag. The concept originates from the theoretical work of Ludwig Prandtl and his student Theodor Meyer in the early 20th century, providing a foundational understanding of supersonic flow phenomena.
