I am trying to evaluate (replacement) two-element airfoils (inverted) for a historic, 1975 Formula 5000 race car. This is a real project, and this car runs near 200 MPH so it matters!
I must be doing something wrong as I can’t achieve a CFD where I believe the results. I’m getting CL in the range of -0.2 and CD +0.3. I’ve tried different AoA, different airfoil profiles, results always the same with physics that can’t be right
mainplane chord = 0.5 m, flap C = 0.2 m
Extrusion in Z = 0.002 m. L dir = Y, airflow dir = X
In my most recent Simulation 7, which I believe is the most correct in terms of simulation settings and approach, I used mesh refinement of 0.00075 m cells on all airfoil surfaces except XY planar. Earlier simulations did not have mesh refinement.
Forces and moments assigned to all airfoil surfaces except XY planar.
Link to project:
Lola T400 Rear Wing | SimScale Workbench
I need someone with experience to help me get to a point where I know how to execute a CFD correctly, i.e. to point out my errors. I started from a near zero knowledge base, only my courses in chemical engineering fluid mechanics in the 1980s!
Thank you in advance
It is harder and it takes longer to provide support without full details.To speed up the process and quickly solve your issues this is a reminder to post as much information as you possibly can:
- A description of the project and what you are trying to achieve
- An description of what is happening, screenshots or error logs are helpful
- [Important] Always provide a link to your project so that it is easy to find.
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