Similarly shaped airfoils to SC(2)-0412
New! Bulk download of polars in Excel format: sc20412.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. RAE 6-9CK
3. RAE 2822
4. SC(2)-0712
5. DSMA-523B
6. DSMA-523A
7. WHITCOMB INTEGRAL SUPERCRITICAL
8. NACA64-113
9. NACA63-113
10. NACA64-113 a=0.8
11. NACA64(1)-112
12. NACA63A112
13. NACA63-113 a=0.8
14. NACA64-112
15. NACA63-112
16. NACA64-112 a=0.8
17. NACA64A112
18. NACA63-112 a=0.8
19. NACA65-112
20. NACA63A113
21. NACA65-112 a=0.8