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