Similarly shaped airfoils to NACA63A216
New! Bulk download of polars in Excel format: NACA63A216.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (3) | 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. P-51D ROOT (BL17.5)
3. NACA65-216 a=0.8
4. NACA64-216 a=0.8
5. NACA65-216 a=0.6
6. NACA65-216
7. NACA64-216 a=0.6
8. NACA65-216 a=0.5
9. NACA64-217 a=0.8
10. AS5046 (16%)
11. NACA63A217
12. NACA63A215
13. NACA64-216
14. NACA64-216 a=0.5
15. NACA64A217
16. NACA64-217 a=0.6
17. NACA64-316
18. NACA64A215
19. NACA65-316
20. NACA64-217
21. NACA64-217 a=0.5