Similarly shaped airfoils to NACA64-720 a=0.2
New! Bulk download of polars in Excel format: NACA64-720%20a%3D0.2.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. NACA64-720 a=0.0
3. NACA63-720 a=0.0
4. NACA64-719 a=0.2
5. NACA63-719 a=0.2
6. NACA64-620 a=0.2
7. NACA64-719 a=0.0
8. NACA63-620 a=0.2
9. NACA63-719 a=0.0
10. NACA65-720 a=0.2
11. NACA64-620 a=0.5
12. NACA65-720 a=0.0
13. NACA65-719 a=0.0
14. NACA65-719 a=0.2
15. NACA64-619 a=0.2
16. NACA63-620 a=0.5
17. NACA63-619 a=0.2
18. NACA65-620 a=0.2
19. NACA65-619 a=0.2
20. NACA64-619 a=0.5
21. NACA63-619 a=0.5