[taillanm]

Hi!

I am simulating a hemisphere-cylindrical body at high Mach numbers vor various altitudes and wall temperatures with the gamma Re-theta model to see the transition process.

For a given flight point I launched a laminar case and a transitional case, when I plot the skin friction along the body my transitional values match the laminar ones, in the laminar part of the flow (up to transition)... which is not the case (at least near the stagnation point) for the heat flux distribution (see attached pictures)

Anyone has an idea where it might come from?

Cf.jpg

Flux.jpg