Similarly shaped airfoils to NACA65-618 a=0.8
New! Bulk download of polars in Excel format: NACA65-618%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. NACA64A618
3. NACA65-619 a=0.8
4. NACA63A618
5. NACA65-617 a=0.8
6. NACA65-618 a=0.6
7. NACA64A617
8. NACA64-618 a=0.8
9. NACA65-717
10. NACA65A618
11. NACA65-719
12. NACA65A617
13. NACA63A617
14. NACA64-718
15. EPPLER 1098
16. EPPLER 655
17. NACA65-518 a=0.8
18. NACA64-619 a=0.8
19. NACA65-718 a=0.8
20. NACA64A718
21. EPPLER 1200