Similarly shaped airfoils to NACA65-212 a=0.0
New! Bulk download of polars in Excel format: NACA65-212%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. NACA65-212 a=0.5
3. NACA64-212 a=0.0
4. NACA64-212 a=0.2
5. NACA65-212
6. RC-12(N)1
7. NACA65-212 a=0.6
8. NACA65(1)-212
9. NACA65-112 a=0.5
10. NACA65-112 a=0.6
11. NACA65-212 a=0.8
12. NACA64-212 a=0.5
13. NACA65-213 a=0.0
14. NACA65-112 a=0.2
15. NACA65-211 a=0.0
16. NACA64A212
17. NACA65-112 a=0.8
18. NACA65-213 a=0.2
19. NACA64-212
20. NACA63-212 a=0.0
21. NACA65-211 a=0.2