FX 057-816
New! Bulk download of polars in Excel format: fx057816.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
DXF file of spline and points: download
Lednicer-format DAT file download
VisualFoil-format DAT file download
X,Y,Z CSV file download
Selig-format DAT file (download):
WORTMANN FX 057-816
1.00000000 0.00000000
0.98297000 0.00334000
0.93302000 0.01211000
0.85356000 0.02830000
0.75000000 0.05179000
0.62941000 0.08408000
0.50000000 0.12294000
0.37059000 0.13226000
0.25000000 0.11887000
0.14645000 0.09479000
0.06699000 0.06290000
0.01704000 0.02979000
0.00000000 0.00000000
0.00000000 0.00000000
0.01704000 -0.01353000
0.06699000 -0.02128000
0.14645000 -0.02673000
0.25000000 -0.03019000
0.37059000 -0.02958000
0.50000000 -0.02906000
0.62941000 -0.02728000
0.75000000 -0.01919000
0.85356000 -0.00542000
0.93302000 0.00121000
0.98297000 0.00136000
1.00000000 0.00000000