Similarly shaped airfoils to NACA63-413 a=0.6
New! Bulk download of polars in Excel format: NACA63-413%20a%3D0.6.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. NACA64-413 a=0.6
3. NACA64-413 a=0.5
4. GA 35-313
5. GA 37-313
6. NACA63-413 a=0.8
7. NACA64-413 a=0.8
8. EPPLER 197
9. NACA63-513
10. NACA64-513
11. MS2.5/13GPV
12. PSU-90-125WL
13. GA 35A313
14. NACA63-414 a=0.6
15. NACA63-412 a=0.6
16. RAF 38
17. NACA63-412 a=0.5
18. NACA64-412 a=0.6
19. NACA64-414 a=0.6
20. NACA63-414 a=0.5
21. GA 35-314