Similarly shaped airfoils to NACA66-015
New! Bulk download of polars in Excel format: NACA66-015.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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
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2. NACA66-115
3. NACA66-115 a=0.2
4. NACA66(215)-016
5. LWK 80-150/K25
6. NACA66A115
7. NACA66-115 a=0.8
8. NACA66-115 a=0.5
9. NACA66-115 a=0.6
10. NACA66-116 a=0.0
11. GA 40A016
12. NACA66-116
13. GA 40A015
14. NACA66-114 a=0.0
15. GA 40-016
16. NACA65-015
17. GA 40-015
18. NACA66-114
19. NACA66-116 a=0.2
20. NACA65A115
21. NACA66-114 a=0.2