Similarly shaped airfoils to NACA65-620 a=0.2
New! Bulk download of polars in Excel format: NACA65-620%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. NACA65-620 a=0.0
3. NACA65-619 a=0.2
4. NACA65-520 a=0.5
5. NACA65-719 a=0.0
6. NACA65-619 a=0.0
7. NACA65-520 a=0.2
8. NACA65-720 a=0.2
9. NACA64-720 a=0.0
10. NACA64-620 a=0.2
11. GA 40-420
12. GA 40A420
13. NACA65-519 a=0.2
14. NACA65-519 a=0.5
15. NACA64-720 a=0.2
16. NACA65-520 a=0.6
17. NACA64-620 a=0.0
18. NACA65-620 a=0.5
19. NACA65-719 a=0.2
20. GA 37A420
21. NACA65(4)-421 a=0.5