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[average_joe]

Can someone explain to me how the coefficient of lift (CL) vs AoA curve is modeled? When I look at the curve of a model (I use the AAM airfile editor) it just doesn't make sense. I'm used to seeing the curve from CL=0 to max CL at stall as an essentially straight line and at post stall AoAs the value of CL is rapidly decreasing. What I see in the editor and even tables is extreme values of AoA (if you believe AoA is expressed in radians, then the values reach 100+ degrees) and negative values of CL.

I checked in my old college aerodynamics books and I don't see anything like what I see in the .AIR file.

What I'm trying to do is tweak the CL vs AoA of an aircraft in its normal flight regime.

Thanks