Similarly shaped airfoils to NACA66(1)-212
New! Bulk download of polars in Excel format: NACA66%281%29-212.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. NACA66-212 a=0.8
3. NACA66-212
4. NACA 66,2-(1.8)12 A=.6 P-51 TIP
5. NACA66-212 a=0.6
6. NACA66-212 a=0.5
7. NACA65A212
8. NACA66-212 a=0.2
9. NACA66-312
10. NACA66-212 a=0.0
11. NACA67A212
12. NACA67-212 a=0.8
13. NACA67-212
14. NACA66A213
15. NACA66-211
16. NACA66A211
17. NACA66-213 a=0.8
18. NACA66-211 a=0.8
19. NACA66-213
20. NACA65A213
21. NACA65(1)-212