How to obtain multiple cross-section "Cp slice" in panel method？

[刘泽皓]

set the rotor to rotate 20 times ,calculating 400 steps from 0.001714···to0.6857···

And I cut the section into four parts, but the pressure distribution value of the first section is 0, and the pressure distribution of other sections is also very strange. Then,In slc file I find that the calculation result is obtained in the first step 0.001714, which is called Case 2.Why can't I get results from other steps or get a normal stress profile,like this?

[Brandon Litherland]

We will need more information that this to really see what's going on.  Can you upload an example model?

Are you slicing a wing or trying to slice the rotor blades?  I'm a bit surprised that the slicer worked with an unsteady case at all. 

[zehao liu]

I want to obtain the cross-section pressure coefficient by the panel method to verify the Caradonna-Tung example. At present, a reasonable Thrust value is obtained, but the cross-section pressure coefficient is not obtained.Please help me solve the problem.Thank you!

[Brandon Litherland]

The Panel mode doesn't work well with unsteady rotating blades.  Also, your slices aren't rotating with the blade frame so you won't get meaningful results this way.  Another approach that *might* work is to run the axisymmetric frame rotation method using the command line.  This will effectively rotate the entire model about X to produce a result.  I'll have to get back to you on the command line for this but it could work.