Similarly shaped airfoils to NACA64-718
New! Bulk download of polars in Excel format: NACA64-718.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. NACA64-618 a=0.8
3. NACA64(3)-618
4. NACA63-618 a=0.8
5. NACA63(3)-618
6. NACA64-719
7. NACA64-717
8. NACA64-518 a=0.8
9. FX 61-184
10. NACA64-618
11. NACA63-518 a=0.8
12. NACA64-619 a=0.8
13. NACA63-717
14. NACA63-719
15. NACA65-718
16. NACA63-618
17. NACA64-617 a=0.8
18. NACA63A618
19. NACA63A617
20. GA 37-418
21. NACA63-619 a=0.8