This content is taken from the course notes on Hypersonic Aerothermodynamics taught at Stanford University by Dr. Javier Urzay and from the course notes on Hypersonic Aerothermodynamics taught by Professor Francesco Panerai at the University of Illinois at Urbana-Champaign. Please enjoy!
The hypersonic regime is identified by flow phenomena, such as thin shock layers, high-temperature effects, low-density effects, and viscous interactions, that become important and pronounced as Mach number increases. A conventional rule of thumb is considered that defines hypersonic flow as flows above Mach 5. Figure 1 portrays flow fields around varying aerodynamic shapes as Mach number increases.
Even though viscous effects are the essence of hypersonic flows, it is convenient to analyze the limit where the flow is inviscid. In this inviscid limit, we will neglect transport phenomena such as viscosity, thermal conduction, diffusion, and high temperature effects. We treat the hypersonic problem from a pure fluid dynamic point of view.
The integral form of conservation equation across an oblique shock take these forms.
The figure below presents the oblique shock geometry
The integral form of conservation equation across an oblique shock equations lead to the Rankine-Hugoniot jump conditions:
