The modification of the original E-CUSP scheme to remove the temperature oscillation with low numerical dissipation was analyzed. It was found that the pressure term in the energy equation dissipation of the original scheme was replaced by the total enthalpy in the modified scheme. For a Mach 2.0 supersonic adiabatic laminar flat-plate boundary layer, the new scheme was able to accurately resolve the boundary-layer velocity and temperature profiles. Results show that the temperature oscillations generated by the original CUSP scheme is also removed.
ASJC Scopus subject areas
- Aerospace Engineering