Similarly shaped airfoils to R140 12.04% (smoothed)
New! Bulk download of polars in Excel format: r140sm.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.
2. NACA65-112 a=0.0
3. NACA65A112
4. NACA65-112 a=0.2
5. NACA65-112
6. NACA64A112
7. NACA65-112 a=0.5
8. NACA65-112 a=0.6
9. NACA65-112 a=0.8
10. NACA63A112
11. NACA64-012A
12. GA 37A012
13. GA 40A012
14. NACA66-112 a=0.0
15. NACA65-012
16. NACA66-112 a=0.2
17. NACA66-112
18. GA 40-012
19. NACA65A111
20. NACA66-112 a=0.5
21. NACA63-012A