Similarly shaped airfoils to NACA64-311 a=0.0
New! Bulk download of polars in Excel format: NACA64-311%20a%3D0.0.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. NACA64-311 a=0.2
3. NACA63-311 a=0.2
4. NACA65-311 a=0.0
5. GA 37-211
6. NACA65-311 a=0.2
7. NACA64-211 a=0.5
8. GA 35-211
9. NACA63-211 a=0.5
10. GA 35A211
11. NACA64-211 a=0.6
12. GA 40-211
13. NACA64-211 a=0.2
14. GA 40A211
15. GA 37A211
16. NACA63-211 a=0.6
17. BOEING 737 OUTBOARD
18. NACA63-211 a=0.2
19. NACA65-211 a=0.5
20. NACA64-312 a=0.0
21. NACA64-310 a=0.0