Similarly shaped airfoils to NACA65-712 a=0.6
New! Bulk download of polars in Excel format: NACA65-712%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. NACA64-712 a=0.6
3. NACA64-712 a=0.5
4. NACA65-713 a=0.6
5. NACA65-711 a=0.6
6. NACA63-712 a=0.6
7. GA 40-612
8. GA 40A612
9. NACA64-713 a=0.6
10. GA 37A612
11. NACA66-712 a=0.6
12. NACA66-711 a=0.6
13. NACA65-711 a=0.5
14. NACA65-712 a=0.8
15. NACA65-713 a=0.5
16. GA 35A612
17. NACA63-712 a=0.5
18. NACA66-712 a=0.5
19. NACA64-713 a=0.5
20. NACA66-711 a=0.5
21. GA 37-612