Similarly shaped airfoils to NACA63A510
New! Bulk download of polars in Excel format: NACA63A510.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. NACA64-510 a=0.8
3. NACA65-510 a=0.8
4. NACA64-610
5. NACA65-610
6. NACA63-510 a=0.8
7. NACA65A510
8. NACA63-610
9. HQ 3.0/10
10. NACA64-511 a=0.8
11. EM J8 3010 DrW
12. NACA64-611
13. GOE 595
14. SB96 10.5/3.0
15. NACA63-511 a=0.8
16. NACA63A511
17. EM J19 3010
18. NACA63A509
19. NACA64A511
20. NACA63-611
21. NACA64-510 a=0.6