EPPLER 49
New! Bulk download of polars in Excel format: e49.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):
EPPLER 49 AIRFOIL
0.99980000 -0.02167000
0.99644000 -0.02006000
0.98716000 -0.01499000
0.93761000 0.01589000
0.89035000 0.03768000
0.66748000 0.08261000
0.62188000 0.08701000
0.38412000 0.09264000
0.29325000 0.08713000
0.13838000 0.06466000
0.05712000 0.03995000
0.03759000 0.03085000
0.01045000 0.01342000
0.00305000 0.00588000
0.00000000 0.00000000
0.00000000 0.00000000
0.00210000 -0.00331000
0.01080000 -0.00493000
0.33341000 0.01826000
0.38996000 0.02057000
0.44818000 0.02203000
0.78599000 0.01137000
0.98540000 -0.01769000
0.99619000 -0.02059000
0.99980000 -0.02167000