Similarly shaped airfoils to NACA66-612 a=0.6
New! Bulk download of polars in Excel format: NACA66-612%20a%3D0.6.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. NACA67-612 a=0.6
3. NACA66-612 a=0.8
4. NACA66-613 a=0.6
5. NACA66-611 a=0.6
6. NACA67-611 a=0.6
7. NACA66A612
8. NACA65-612 a=0.6
9. FX 74-130 WP2 MOD
10. FX 74-130 WP2
11. NACA67-612 a=0.5
12. NACA66-611 a=0.5
13. NACA66-613 a=0.5
14. NACA67-611 a=0.5
15. NACA65-613 a=0.6
16. AH 80-129
17. NACA65-612 a=0.5
18. NACA65A612
19. AH 88-K-130/20
20. NACA66-712
21. NACA65-613 a=0.5