Hi, i'm running an airfoil simulation in the cfd code Fluent. After my solutions converged, i viewed the Coefficient of pressure plot for my aerofoil. The maximum Cp is more than 1. This does not make sense according to Bernoulli's equations. Can anybody help?

Rif

Did you set the right reference values? Also, depending on how far away your boundaries are, and exactly what BC's you specify, it is possible to get a horisontal pressure gradient effect that would show up in a slightly higher stagnation pressure coefficient.

If it is compressible flow, then you can get more than one. Back to basic gas dynamics, read Anderson or some such book.

It is NOT a compressible flow. My density is constant.

Rif