Similarly shaped airfoils to NACA63-410 a=0.0
New! Bulk download of polars in Excel format: NACA63-410%20a%3D0.0.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. NACA63-410 a=0.2
3. NACA64-410 a=0.2
4. NACA63-310 a=0.5
5. NACA63-310 a=0.2
6. NACA65-410 a=0.0
7. NACA64-310 a=0.5
8. NACA64-310 a=0.2
9. S3016-095-87
10. MS2-9,5
11. NACA65-410 a=0.2
12. NACA63-411 a=0.0
13. NACA63-409 a=0.0
14. NACA63-310 a=0.6
15. RC(5)-10
16. NACA64-409 a=0.0
17. NACA64-411 a=0.0
18. TT54
19. TL54
20. GA 35-210
21. NACA63-411 a=0.2