Similarly shaped airfoils to NACA65-320 a=0.8
New! Bulk download of polars in Excel format: NACA65-320%20a%3D0.8.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. NACA65-320 a=0.6
3. NACA65-320
4. GA 40-220
5. NACA65-320 a=0.5
6. GA 40A220
7. NACA64A320
8. NACA65-319 a=0.8
9. NACA65-421
10. NACA65-419
11. NACA63A320
12. NACA65-319 a=0.6
13. GA 37A220
14. NACA64A319
15. GA 40-219
16. GA 40A219
17. NACA65-319
18. NACA65-319 a=0.5
19. NACA65-220 a=0.6
20. GA 37-220
21. NACA65-220 a=0.8