Similarly shaped airfoils to S1014
New! Bulk download of polars in Excel format: s1014.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
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2. GA 40-017
3. GA 40A018
4. GA 40-018
5. GA 37A017
6. NACA66-117 a=0.0
7. NACA66-117
8. NACA65-018
9. S1016
10. NACA66(215)-016
11. NACA66-117 a=0.2
12. GA 37A018
13. NACA66A117
14. NACA66-018
15. NACA65A117
16. NACA66-117 a=0.8
17. NACA66-117 a=0.5
18. GA 35A017
19. NACA66-117 a=0.6
20. NACA63A017
21. NACA65-118 a=0.0