Similarly shaped airfoils to NACA65-720 a=0.5
New! Bulk download of polars in Excel format: NACA65-720%20a%3D0.5.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
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2. GA 40-620
3. GA 40A620
4. NACA65-719 a=0.5
5. GA 37A620
6. NACA65-719 a=0.6
7. GA 40-619
8. GA 40A619
9. NACA64-720 a=0.5
10. GA 35A620
11. GA 37-620
12. GA 37A619
13. NACA65-620 a=0.5
14. NACA65-620 a=0.6
15. NACA64-720 a=0.6
16. GA 35A619
17. NACA65-619 a=0.5
18. NACA65-619 a=0.6
19. NACA65-720 a=0.8
20. NACA64-719 a=0.5
21. NACA66-719 a=0.5