Supersonic Airfoil Flow Simulation - Mach Number and Vorticity Visualization #1242434 (License: Personal Use)

The top panel visualizes Mach number contours around a symmetric airfoil in supersonic flow, with red indicating shock formation near the leading edge and yellow-green regions representing expansion fans. The bottom panel displays the corresponding vorticity field (μt), where intense color gradients along the trailing edge reveal strong shear layers and vortex shedding in the wake. Both plots are derived from steady-state Navier-Stokes simulations using finite-volume methods.

Used in aerospace engineering education, research publications, and CFD software documentation to illustrate compressible flow phenomena; targets students, researchers, and aerodynamic designers seeking to understand shock-boundary layer interaction.