Similarly shaped airfoils to NACA63-511 a=0.8
New! Bulk download of polars in Excel format: NACA63-511%20a%3D0.8.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. NACA63-611
3. NACA64-611
4. NACA63A511
5. HQ 3.0/11
6. NACA63-511 a=0.6
7. NACA64-511 a=0.6
8. NACA64A511
9. SB96 10.5/3.0
10. NACA65-511 a=0.8
11. NACA63-512 a=0.8
12. NACA63-510 a=0.8
13. NACA63A510
14. NACA65-611
15. K3311 (smoothed)
16. NACA64-510 a=0.8
17. NACA64-512 a=0.8
18. K3311 (original)
19. NACA63-612
20. HQ 3.0/10
21. NACA63-610