getting Positive Cm instead of negative: flow over airfoil
 

hello,
i'm currently simulating flow over a super critical airfoil with mach number 0.729 and AOA=2.79 degree. Comparing my results with experimental data of AGARD, i found all my result matching except the Cm. It should be -0.09 but every time i'm getting +0.09. Can anyone help me please?

I used S-A model and solver was pressure based.
I need to know the answers urgently....

thanks in advance for your reply.