Compressible Analysis for Drag & Temperature | SimScale Workbench
I am a college student using the Compressible simulation to investigate how varying nose radii affects the trade-off between thermal protection and aerodynamic drag in hypersonic flow for aircraft from Mach 5 to 10. While simulating Mach 7, my solver diverges especially with my pressure values sometimes going from 10,000+ Pa to 500,000+ Pa, and my residual values are Nan. Could someone please help me to inspect for errors, I have already enabled “Share with support.” Thank you.