Similarly shaped airfoils to NACA64-720 a=0.8
New! Bulk download of polars in Excel format: NACA64-720%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. NACA64-719 a=0.8
3. NACA63-719 a=0.8
4. NACA63A719
5. NACA64-720 a=0.6
6. NACA63A720
7. NACA65-720 a=0.8
8. NACA64-620 a=0.8
9. NACA63-620 a=0.8
10. FX 66-S-196
11. NACA63-720 a=0.6
12. NACA64A719
13. NACA65-719 a=0.8
14. FX 66-S-196 V1
15. NACA64A720
16. NACA64-620 a=0.6
17. NACA63-620 a=0.6
18. FX S 02-196
19. NACA64-619 a=0.8
20. NACA64-719 a=0.6
21. NACA63-619 a=0.8