NACA44015


Direct link: NACA44015
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 points: download
Lednicer-format DAT file download
VisualFoil-format DAT file download
X,Y,Z CSV file download
Selig-format DAT file (download):

NACA44015
1.00236798 -0.01031049
1.00220897 -0.01025365
1.00147608 -0.01008285
1.00025539 -0.00979863
0.99854809 -0.00940168
0.99635581 -0.00889291
0.99368070 -0.00827353
0.99052535 -0.00754498
0.98689282 -0.00670894
0.98278663 -0.00576732
0.97821077 -0.00472226
0.97316969 -0.00357610
0.96766829 -0.00233139
0.96171191 -0.00099083
0.95530634 0.00044268
0.94845782 0.00196610
0.94117302 0.00357625
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1.00004253 -0.01058178
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1.00203355 -0.01034083
1.00236798 -0.01031049