Similarly shaped airfoils to NACA63-620 a=0.6
New! Bulk download of polars in Excel format: NACA63-620%20a%3D0.6.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. NACA64-620 a=0.6
3. NACA64-620 a=0.5
4. NACA63-619 a=0.6
5. NACA63-620 a=0.8
6. NACA63-619 a=0.5
7. NACA64-619 a=0.6
8. GA 35-420
9. NACA64-620 a=0.8
10. NACA64-619 a=0.5
11. NACA63-520 a=0.6
12. NACA63-720 a=0.5
13. NACA63-720 a=0.6
14. NACA63-720
15. NACA64-720 a=0.6
16. NACA64-720 a=0.5
17. GA 37-420
18. NACA63-619 a=0.8
19. GA 35-419
20. NACA64-720
21. NACA63-720 a=0.8