Similarly shaped airfoils to NACA63-718 a=0.5
New! Bulk download of polars in Excel format: NACA63-718%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. NACA63-718 a=0.6
3. GA 35-618
4. NACA64-718 a=0.6
5. GA 37-618
6. NACA63-719 a=0.5
7. NACA63-717 a=0.5
8. NACA64-717 a=0.5
9. NACA64-719 a=0.5
10. NACA63-719 a=0.6
11. NACA63-717 a=0.6
12. GA 35-617
13. NACA64-719 a=0.6
14. GA 35-619
15. NACA64-717 a=0.6
16. NACA63-618 a=0.5
17. GA 37-617
18. NACA63-618 a=0.6
19. GA 37-619
20. FX 84-W-175
21. GA 35A617