Similarly shaped airfoils to NACA65-320 a=0.0


Direct link: NACA65-320 a=0.0
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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1. NACA65-320 a=0.2
2. NACA65-220 a=0.5
3. NACA65-220 a=0.2
4. NACA65-220 a=0.6
5. NACA65-220 a=0.0
6. NACA65-319 a=0.0
7. NACA65-420 a=0.0
8. NACA65-319 a=0.2
9. NACA65-220 a=0.8
10. NACA65-320 a=0.5
11. NACA65-219 a=0.5
12. NACA65-320
13. NACA65-219 a=0.2
14. NACA64-320 a=0.0
15. NACA64-320 a=0.2
16. NACA65-220
17. NACA65-219 a=0.6
18. GA 40-220
19. NACA65-320 a=0.6
20. NACA65-219 a=0.0
21. NACA64A220