Similarly shaped airfoils to NACA63-510 a=0.8
New! Bulk download of polars in Excel format: NACA63-510%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. NACA63-610
3. NACA64-610
4. NACA63A510
5. HQ 3.0/10
6. EM J8 3010 DrW
7. NACA64A510
8. EM J19 3010
9. NACA65-510 a=0.8
10. NACA63-510 a=0.6
11. NACA64-510 a=0.6
12. NACA65-610
13. SB96 10.5/3.0
14. NACA63A509
15. NACA63-511 a=0.8
16. NACA63-509 a=0.8
17. NACA64-509 a=0.8
18. NACA64-511 a=0.8
19. NACA63-611
20. S7075 (9%)
21. NACA63-609