Similarly shaped airfoils to SC(2)-0612
New! Bulk download of polars in Excel format: sc20612.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. SC(2)-0412
3. RAE 6-9CK
4. RAE 2822
5. NACA64-113
6. NACA63-113
7. NACA64-113 a=0.8
8. NACA63A112
9. NACA63-113 a=0.8
10. NACA64-112
11. NACA63-112
12. NACA64(1)-112
13. NACA64-112 a=0.8
14. NACA64A112
15. NACA63-112 a=0.8
16. NACA65-112
17. EPPLER EA 6(-1)-012
18. NACA63A113
19. NACA64-113 a=0.6
20. NACA63-113 a=0.6
21. NACA65-112 a=0.8