Similarly shaped airfoils to NACA63-718 a=0.8
New! Bulk download of polars in Excel format: NACA63-718%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. NACA63-719 a=0.8
3. NACA63-717 a=0.8
4. NACA64-717 a=0.8
5. NACA64-719 a=0.8
6. NACA63-718 a=0.6
7. EPPLER 856
8. Dees Okay230
9. NACA64-718 a=0.6
10. NACA63-618 a=0.8
11. NACA63A717
12. NACA63A718
13. GA 35-618
14. NACA64-618 a=0.8
15. NACA63-618 a=0.6
16. FX 84-W-175
17. FX 66-S-196 V1
18. NACA63-717 a=0.6
19. NACA63-719 a=0.6
20. HQ 3.5/18
21. GA 37-618