Similarly shaped airfoils to NACA63-319 a=0.5
New! Bulk download of polars in Excel format: NACA63-319%20a%3D0.5.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. GA 35-219
3. NACA64-319 a=0.5
4. NACA64-319 a=0.6
5. NACA63-319 a=0.8
6. NACA63-419 a=0.0
7. NACA63-319 a=0.2
8. GA 37-219
9. NACA63-419 a=0.2
10. NACA63-419
11. NACA64-319 a=0.8
12. NACA63-320 a=0.5
13. NACA63-318 a=0.5
14. NACA64-419 a=0.0
15. NACA63-320 a=0.6
16. NACA63-318 a=0.6
17. NACA64-419
18. NACA64-419 a=0.2
19. NACA63-319
20. GA 35-218
21. NACA64-319 a=0.2