Similarly shaped airfoils to S4158
New! Bulk download of polars in Excel format: s4158.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. S7055 (10.5%) Flat-Bottomed
3. NACA64-511 a=0.6
4. Davis
5. NACA65-511 a=0.5
6. NACA64-611 a=0.5
7. NACA64-611 a=0.6
8. NACA63-511 a=0.6
9. NACA65-611 a=0.5
10. NACA64-511 a=0.5
11. NACA65-611 a=0.6
12. NACA64-612 a=0.6
13. NACA64-612 a=0.5
14. NACA63-611 a=0.5
15. NACA63-611 a=0.6
16. NACA64-512 a=0.6
17. NACA63A611
18. NACA63-511 a=0.5
19. GA 35A411
20. NACA63-612 a=0.6
21. JWL041 11/3.5