Learning Forum

[w d]

Hi, been struggling to find the solution for this for a while, under all flow conditions it complains that the wall is too close to an outlet even though it's 20c downstream and 10 C above and below.

I get results but best i can get is CD is about 60% higher than it should be compared to data from theory of wing sections.

if i try running it at m 1.2 there's a triangle of very high speed flow in the bottom right of the enclosure, and i can only run this at 0 aoa otherwise it just throws an error about the max mach number going up to mach 7 or so, then crashes

Using cartesian components to simulate AoA so front and bottom are inflow and top and back are outflow.

I'm really out of ideas here...

 

[C N]

Hello

I suggest you to refer this Ansys innovation course on compressible flow over airfoil simulation set up. Hope this will solve your problem 

Airfoil Simulation Example | Ansys Courses

Thanks