Similarly shaped airfoils to NACA65A719


New! Bulk download of polars in Excel format: NACA65A719.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
Dynamic plotter New!
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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1. NACA65A720
2. NACA65A718
3. NACA64A719
4. NACA66-719 a=0.8
5. NACA66A719
6. NACA65-719 a=0.8
7. NACA64A720
8. NACA66A718
9. NACA66-718 a=0.8
10. NACA65-720 a=0.8
11. NACA65A619
12. NACA63A719
13. NACA64A718
14. NACA66-719 a=0.6
15. NACA65A618
16. NACA63A720
17. NACA66-720 a=0.8
18. NACA65A620
19. NACA66A720
20. NACA66-619 a=0.8
21. NACA65-719 a=0.6