03.1 - Aerodynamics – CFD Methods and Validation
ACCURATE TWO-DIMENSIONAL STEADY-STATES FOR THE SUPERSONIC FLOW OVER A COMPRESSION CORNER
R. Santos¹, L. Alves¹, N. Cerulus², H. Quintanilha Jr², V. Theofilis²; ¹UFF, Brazil ;²UoL, United Kingdom
The present paper describes the numerical issues that had to be overcome in order to generate of accurate steady-states for the supersonic flow over a compression corner. Low-order schemes generate steady-states contaminated by temporal content. Switching to high-order schemes, however, eventually leads to disturbance free steady-states.