Similarly shaped airfoils to NACA67-713 a=0.8
New! Bulk download of polars in Excel format: NACA67-713%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
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. NACA67-714 a=0.8
3. NACA67-712 a=0.8
4. NACA67A712
5. NACA66-713 a=0.8
6. NACA66A713
7. NACA67A714
8. NACA66-714 a=0.8
9. NACA67-713 a=0.6
10. NACA66A714
11. NACA67-613 a=0.8
12. NACA65A714
13. NACA67-613 a=0.6
14. NACA67A613
15. NACA65A713
16. NACA67-714 a=0.6
17. NACA67-712 a=0.6
18. NACA66-713 a=0.6
19. NACA67-612 a=0.8
20. NACA66-613 a=0.8
21. NACA66-714 a=0.6