Similarly shaped airfoils to NACA63(2)A-015
New! Bulk download of polars in Excel format: NACA63%282%29A-015.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. NACA65-315 a=0.0
3. NACA25014.5
4. NACA64-315 a=0.2
5. NACA25015
6. NACA2215
7. NACA65-315 a=0.2
8. NACA64-316 a=0.0
9. NACA63-315 a=0.0
10. GA 35A215
11. NACA64-316 a=0.2
12. NACA65-215 a=0.2
13. Falcon (Carl Goldberg Falcon 56 Mk II R/C powerplane)
14. GA 37A215
15. NACA63-315 a=0.2
16. NACA64-215 a=0.2
17. NACA25014
18. NACA63-316 a=0.0
19. NACA65-316 a=0.0
20. NACA65-215 a=0.5
21. NACA63A215