Similarly shaped airfoils to NACA63A720
New! Bulk download of polars in Excel format: NACA63A720.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. NACA63A719
3. NACA65-720 a=0.8
4. NACA64A719
5. NACA64-720 a=0.8
6. NACA63A620
7. NACA64A620
8. GA 35A620
9. NACA65A720
10. NACA63-720 a=0.8
11. NACA65-620 a=0.8
12. NACA63A619
13. GA 37A620
14. NACA65-719 a=0.8
15. NACA64A619
16. NACA65A719
17. NACA65-720 a=0.6
18. NACA64-720 a=0.6
19. NACA65-620 a=0.6
20. GA 35A619
21. GA 40A620