Similarly shaped airfoils to NACA65-712 a=0.5
New! Bulk download of polars in Excel format: NACA65-712%20a%3D0.5.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=0.5
3. GA 40-612
4. GA 40A612
5. NACA64-712 a=0.6
6. GA 37A612
7. NACA65-713 a=0.5
8. NACA65-711 a=0.5
9. NACA63-712 a=0.5
10. GA 35A612
11. NACA64-713 a=0.5
12. NACA66-712 a=0.5
13. GA 37-612
14. NACA65-713 a=0.6
15. NACA66-711 a=0.5
16. NACA63-712 a=0.6
17. NACA65-711 a=0.6
18. NACA64-713 a=0.6
19. GA 40-613
20. GA 40A613
21. NACA66-712 a=0.6