Similarly shaped airfoils to NACA63-210 a=0.2
New! Bulk download of polars in Excel format: NACA63-210%20a%3D0.2.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. NACA64-210 a=0.2
3. NACA64-210 a=0.0
4. NACA63-210 a=0.5
5. NACA64-210 a=0.5
6. NACA63-210 a=0.6
7. NACA64-210 a=0.6
8. HQ 1.0/10
9. NACA63-210
10. NACA64-210
11. NACA63-210 a=0.8
12. MH 61 10.26%
13. NACA65-210 a=0.2
14. NACA65-210 a=0.0
15. NACA64-210 a=0.8
16. Ritz 1-30-10
17. NACA63-310 a=0.0
18. NACA64-310 a=0.0
19. NACA63-211 a=0.2
20. NACA63-209 a=0.2
21. RC-10(N)1