Joukowsky 16.00% thick 1.00% camber


New! Bulk download of polars in Excel format: Joukowsky%2016.00%25%20thick%201.00%25%20camber.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
Dynamic plotter New!
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.


Angle (deg),
positive is trailing edge down
DAT File
5Joukowsky 16.00% thick 1.00% camberFLAP5C25
15Joukowsky 16.00% thick 1.00% camberFLAP15C25
25Joukowsky 16.00% thick 1.00% camberFLAP25C25
35Joukowsky 16.00% thick 1.00% camberFLAP35C25
45Joukowsky 16.00% thick 1.00% camberFLAP45C25
-5Joukowsky 16.00% thick 1.00% camberFLAPM5C25
-15Joukowsky 16.00% thick 1.00% camberFLAPM15C25
-25Joukowsky 16.00% thick 1.00% camberFLAPM25C25
-35Joukowsky 16.00% thick 1.00% camberFLAPM35C25
-45Joukowsky 16.00% thick 1.00% camberFLAPM45C25