Similarly shaped airfoils to NACA63-215 MOD B
New! Bulk download of polars in Excel format: n63215b.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. NACA63-316
3. NACA63-315
4. NACA2215
5. NACA63-315 a=0.0
6. NACA63-216 a=0.6
7. NACA63-215 a=0.6
8. NACA63-316 a=0.0
9. NACA63-216 a=0.8
10. NACA63-215 a=0.8
11. NACA63-215 a=0.5
12. NACA63-216 a=0.5
13. GA 35-216
14. NACA63-316 a=0.2
15. GA 35-215
16. NACA63-315 a=0.2
17. GA 30-215
18. NACA63-215 a=0.2
19. NACA63-216 a=0.2
20. NACA63(2)A-015
21. NACA2315