Similarly shaped airfoils to NACA65A519


New! Bulk download of polars in Excel format: NACA65A519.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. NACA65A520
2. NACA65A518
3. NACA64A519
4. NACA66-519 a=0.8
5. NACA66A519
6. NACA66-619
7. NACA65-519 a=0.8
8. NACA64A520
9. NACA65-619
10. FX 05-191
11. NACA66-518 a=0.8
12. NACA66A518
13. NACA65A419
14. NACA66-618
15. NACA65-520 a=0.8
16. NACA65A619
17. NACA65-620
18. FX 70-VC-194/2.0
19. NACA66-519 a=0.6
20. NACA66-719
21. NACA63A519