Similarly shaped airfoils to NACA65-720 a=0.6
New! Bulk download of polars in Excel format: NACA65-720%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. GA 40-620
3. GA 40A620
4. NACA65-719 a=0.6
5. GA 37A620
6. NACA65-719 a=0.5
7. NACA65-720 a=0.8
8. GA 40-619
9. GA 40A619
10. NACA64-720 a=0.6
11. GA 35A620
12. GA 37-620
13. GA 37A619
14. NACA65-620 a=0.6
15. NACA64-720 a=0.5
16. NACA64A720
17. GA 35A619
18. NACA65-719 a=0.8
19. NACA65-620 a=0.5
20. NACA65-619 a=0.6
21. NACA63A720