In general, the physical behavior of compressible flows is more complicated than in incompressible flows. Compressible flows may be viscous or inviscid, depending on flow velocities. Compressible inviscid flows are analyzed using the potential or Euler equations, whereas compressible viscous flows are solved from the Navier-Stokes system of equations. Shock waves may occur in compressible flows and require special attention as to the solution methods. Furthermore, shock wave turbulent boundary layer interactions in compressible viscous flows constitute one of the most important physical phenomena in computational fluid dynamics. Let us consider air flows at speeds greater than 100 m/s, which corresponds to a Mach number of approximately 0.3, but less than 1700 m/s, or approximately Mach 5. Air flows in this range (0.3 ≤M ≤5) may be considered as compressible and inviscid. This range is usually subdivided into regions identified as subsonic (0.3 < M <0.8), transonic (0.8 ≤ M ≤1.2), and supersonic (1.2<M?5). For M > 5, the flow is referred to as hypersonic. Hypersonic flows around a solid body are usually coupled with viscous boundary layers. Effects of dilatational dissipation due to compressibility, high temperature gradients, vortical motions within the secondary boundary layers, radiative heat transfer, vibrational and electronic energies, and chemical reactions are examples of some of the complex physical phenomena associated with hypersonic flows.

In order to take into account the compressibility and variations of density in highspeed flows, we utilize the conservation form of the governing equations, using the density-based formulation.