Similarly shaped airfoils to NACA64-720 a=0.6
New! Bulk download of polars in Excel format: NACA64-720%20a%3D0.6.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=0.5
3. NACA63-720 a=0.5
4. GA 37-620
5. NACA64-719 a=0.6
6. GA 35-620
7. NACA64-719 a=0.5
8. NACA63-719 a=0.6
9. NACA64-720 a=0.8
10. NACA63-719 a=0.5
11. NACA65-720 a=0.6
12. GA 37-619
13. NACA63-720 a=0.8
14. NACA64-620 a=0.6
15. NACA63-620 a=0.6
16. NACA65-720 a=0.5
17. GA 35-619
18. NACA65-719 a=0.6
19. GA 35A619
20. NACA65-719 a=0.5
21. GA 35A620