Similarly shaped airfoils to NACA63-209 a=0.5
New! Bulk download of polars in Excel format: NACA63-209%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. NACA64-209 a=0.5
3. NACA64-209 a=0.6
4. NACA63-209 a=0.8
5. NACA63-209 a=0.2
6. NACA64-209 a=0.8
7. NACA64-209 a=0.2
8. NACA63-209 a=0.0
9. NACA64-209 a=0.0
10. NACA63-209
11. HQ 1.0/9
12. NACA65-209 a=0.5
13. NACA63A209
14. NACA64-209
15. NACA65-209 a=0.6
16. NACA63-309 a=0.0
17. TP66-S tip
18. HQ 1.5/8.5
19. NACA63-309
20. HQ 1.5/9
21. HQ 1.5/9 B