Similarly shaped airfoils to NACA65-718 a=0.6
New! Bulk download of polars in Excel format: NACA65-718%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. GA 40-618
3. GA 40A618
4. NACA65-719 a=0.6
5. NACA65-717 a=0.6
6. GA 37A618
7. NACA64-718 a=0.6
8. NACA65-717 a=0.5
9. NACA65-718 a=0.8
10. NACA65-719 a=0.5
11. GA 35A618
12. FX 84-W-175
13. GA 40-617
14. GA 40A617
15. GA 40-619
16. GA 37-618
17. GA 40A619
18. NACA64-718 a=0.5
19. GA 37A617
20. NACA64-719 a=0.6
21. NACA65-618 a=0.6