Similarly shaped airfoils to NACA64-217 a=0.8
New! Bulk download of polars in Excel format: NACA64-217%20a%3D0.8.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. NACA64-217
3. NACA63-217 a=0.8
4. NACA64-217 a=0.5
5. NACA64-317
6. NACA63-217 a=0.6
7. NACA63-217
8. NACA63-217 a=0.5
9. P-51D ROOT (BL17.5)
10. NACA63-317
11. NACA64-217 a=0.2
12. NACA64-218 a=0.8
13. NACA64-216 a=0.8
14. NACA63A217
15. NACA63-217 a=0.2
16. NACA63A216
17. NACA64-218 a=0.6
18. NACA64-216 a=0.6
19. NACA65-217 a=0.8
20. NACA64(3)-218
21. NACA64-217 a=0.0