Similarly shaped airfoils to NACA67-711 a=0.8
New! Bulk download of polars in Excel format: NACA67-711%20a%3D0.8.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
Dynamic plotter New!
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. GOE 7K
3. NACA66-711 a=0.8
4. NACA66A711
5. NACA67-712 a=0.8
6. NACA67-710 a=0.8
7. NACA66-712 a=0.8
8. NACA67A710
9. NACA66A712
10. NACA67A712
11. NACA67-711 a=0.6
12. NACA65A711
13. NACA65A712
14. NACA67-611 a=0.8
15. GOE 12K
16. NACA66-711 a=0.6
17. NACA67-611 a=0.6
18. NACA67A611
19. NACA66-611 a=0.8
20. NACA67-712 a=0.6
21. NACA66A710