Similarly shaped airfoils to NACA63A215
New! Bulk download of polars in Excel format: NACA63A215.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. NACA65-215 a=0.8
3. NACA64-215 a=0.8
4. NACA65(2)-215
5. NACA64(2)-215
6. NACA65-215 a=0.6
7. NACA65-215
8. NACA64-215 a=0.6
9. NACA65-215 a=0.5
10. NACA64-215
11. NACA64-216 a=0.8
12. NACA64-215 a=0.5
13. NACA63A216
14. NACA63A214
15. NACA64-216 a=0.6
16. NACA64A216
17. NACA64-315
18. NACA65-315
19. NACA63-215 a=0.8
20. NACA64-216
21. NACA64A214