Problems working with Javafoil, stagnation point location is way off?

Hi everyone,

Was hoping I could get some help with a project I'm working on with Javafoil. I would like to get the Cp distribution around my airfoils but for some reason when I run Javafoil I keep getting Cp of 1 on the upper surface and large negative values on the underside. Its almost as if the flow were being directed vertically down. I would expect the stagnation point at the leading edge but it seems to be over the whole upper surface instead. When I view the streamlines I can see the results are not very realistic. Does anyone have experience with this, is there a setting I'm missing somewhere?

 

That looks just ok for the kind of high-lift foil you have, but if you expect "lift" as beeing upwards, you have placed your foil upside-down. Now add more streamlines to the upper area (as drawn above); you will find the stagnation point at about the "top" point of the leading edge.

 

Thanks for your reply. Actually I would expect high downforce from this sort of setup so the orientation is correct. I'm just comparing with some CFD runs I have and I find that I have to adjust these sort of high downforce setups by up to 15 degrees to get any sort of similar Cp distribution. Wondering if others have the same experience as me.