Hi! I'm doing an analysis on a 2-D airfoil (fx 63-137) but somehow the lift coefficient i got is -0.0006. I entered my chord length for the area and length for the reference value part. The freestream mach number is 2. The model is invisid. I was told that there is something wrong with the scale under the grid option. I adjusted the domain extent for the scale grid but still i get negative values for lift. Please help me, thank you!

set area as 1 (for 2D) and airfoil chord for length. You scaled you model? make sure your reference values are also based on the scaled model.

Hope it helps