# In xflr5,how is the value of Fz calculated?

I am building an conventional plane with AR=6 and I find the wing area,A.So I have selected an airfoil for building my plane that is sd7062. Using xflr5 I got a cl vs alpha graph and I took the cl value at 4 degrees . using this cl value I calculated my lift and equated to the weight of my plane which is 2kg*9.81=19.6N .now equating L=W I find the area ,A and using this area and aspect ratio 6 or 7 I calculate the span and chord .Now when I do an analysis for the wing dimensions I got and plot a graph between Fz(lift) and alpha graph and find that at 4 degrees the Fz value is 13.078N ....why is there a decrease in my lift.....if there's a decrease then are the calculations I have done wrong?..please help me out]1

• Difference due to 3D effects (finite wing)? Commented Nov 30, 2018 at 10:57
• Sir,can you elaborate please? Commented Jan 10, 2019 at 8:32
• Does your wing have any twist or taper? Commented Jul 31, 2019 at 5:27
• no twist, no taper just a simple rectangular wing... Commented Aug 1, 2019 at 6:03