he Aerodynamic calculation results displayed in VSPAERO results manager revealed discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing.

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Good morning everyone,

i am especially interested in applying of aircraft wing’s pressure distribution estimated in VSPAERO and transform the pressure distribution into  Nastran  discrete Finite Element Modell. 

I built simple wing model in OpenVsp program and run the aerodynamic analysis:   

The Aerodynamic calculation results displayed in VSPAERO results manager revealed discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing. The Calculation of Total Lift Force Lz in calculation spreadsheet according to Cl coefficients stored in file: wing-with-controls.lod showed important change of wing’s Total Lift Force Lz.   

The question:

There is possible to avoid: - above mentioned huge discontinuity in Cl distribution along wing span coordinate Y between wing and controls components (huge difference of Cp distribution on wing between wing and controls components)?

VSPAERO Viewer results for Pressure coefficient Cp distribution:
Pressure coefficient Cp distribution - Wing Pressure coefficient Cp distribution – LHS Flap region enlargement  

  Pressure coefficient Cp distribution – LHS Aileron region enlargement

Best regards