Similarly shaped airfoils to NACA63-310 a=0.0
New! Bulk download of polars in Excel format: NACA63-310%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. NACA63-310 a=0.2
3. NACA64-310 a=0.2
4. GA 35-210
5. GA 37-210
6. NACA63-210 a=0.5
7. MH 44 9.66%
8. NACA64-210 a=0.5
9. NACA65-310 a=0.0
10. GA 35A210
11. NACA63-210 a=0.6
12. Sipkill 1.7/10
13. NACA65-310 a=0.2
14. NACA64-210 a=0.6
15. NACA63-210 a=0.2
16. MH 61 10.26%
17. NACA64-210 a=0.2
18. AZcombat1
19. GA 37A210
20. MH 60 10.08%
21. GA 40-210