Similarly shaped airfoils to NACA64A719
New! Bulk download of polars in Excel format: NACA64A719.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. NACA65-719 a=0.8
3. NACA64A720
4. NACA64A718
5. NACA65A719
6. NACA63A718
7. NACA65-720 a=0.8
8. NACA63A720
9. NACA65A718
10. NACA64A619
11. NACA64-719 a=0.8
12. NACA65-619 a=0.8
13. NACA64-720 a=0.8
14. NACA65-718 a=0.8
15. NACA63A619
16. GA 37A619
17. NACA65-719 a=0.6
18. NACA65A619
19. GA 35A619
20. NACA64A618
21. NACA65-619 a=0.6