Xfoil

An example input file to run Xfoil, derive the airfoil cross-sectional aera moment inertia and the aerodynamic lift, drag and moment coefficients.

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RUN XFOIL AS FOLLOWS:

xfoil.exe < xfoil_input.cmd > xfoil_output.out

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REQUIRED INPUT FILES:

• xfoil_input.cmd : XFOIL COMMANDS

• AIRFOIL_GEO.DAT : ACTUAL AIRFOIL GEOMETRY STARTING FROM TRAILING EDGE (BACK) SIDE OF THE AIRFOIL SECTION : USE THIS TO COMPUTE THE ACTUAL INERTIA OF THE AIRFOIL CROSS-SECTOPM

• AIRFOIL_GEO_NORMALIZED.DAT : NORMALIZED AIRFOIL GEOMETRY STARTING FROM TRAILING EDGE (BACK) SIDE OF THE AIRFOIL SECTION : USE THIS TO THE AERODYNAMIC LIFT, DRAG AND MOMENT COEFFICIENTS

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OUPUT:

• xfoil_output.out : XFOIL OUTPUT, INCLUDING MOMENTS OF INERTIA
• XFOILAIRFOIL.dat : XFOIL DISCRITIZED AIRFOIL
• AIRFOIL_POLARS.dat : XFOIL COMPUTED POLARS, LIFT, DRAG AND MOMENT COEFFICIENTS

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RESOURCES:

https://web.mit.edu/drela/Public/web/xfoil/

http://web.mit.edu/aeroutil_v1.0/xfoil_doc.txt