Abstract:
A supersonic flow in the near wake behind a cylinder is considered. Pressure distributions in the base region behind a circular cylinder for various Mach numbers $\mathrm{M}_\infty$ are obtained and analyzed by means of direct numerical simulation based on high-order approximation algorithms. For $\mathrm{M}_\infty=2.46$, the results obtained in the present study are compared with available experimental and numerical data. Generation of turbulent kinetic energy is calculated for various Mach numbers.
Keywords:supersonic flow, Navier–Stokes equations, high-order approximation, direct numerical simulation, base drag.
Fulltext:
PDF file (715 kB)