Similarly shaped airfoils to NACA65-312 a=0.0
New! Bulk download of polars in Excel format: NACA65-312%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. NACA64-312 a=0.0
3. GA 40-212
4. GA 40A212
5. NACA64-312 a=0.2
6. NACA65-212 a=0.5
7. NACA65(1)-212 a=0.6
8. Europa Dykins 12%
9. GA 37A212
10. NACA65-212 a=0.6
11. MH 18B
12. NACA65-212 a=0.2
13. RC-12(N)1
14. GA 35A212
15. NACA65-313 a=0.0
16. NACA65-311 a=0.0
17. NACA63-312 a=0.0
18. NACA65-313 a=0.2
19. NACA65-312 a=0.5
20. NACA64-212 a=0.5
21. NACA63-312 a=0.2