Similarly shaped airfoils to NACA64A616
New! Bulk download of polars in Excel format: NACA64A616.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. NACA65-616 a=0.8
3. NACA65-716
4. NACA65A616
5. NACA64A617
6. NACA64A615
7. NACA63A615
8. NACA64-616 a=0.8
9. NACA65-617 a=0.8
10. NACA65A615
11. NACA63A617
12. NACA64-716
13. NACA65-717
14. NACA64-617 a=0.8
15. GOE 493
16. NACA65-616 a=0.6
17. NACA64-717
18. NACA65-615 a=0.8
19. NACA65-516 a=0.8
20. FX 60-160
21. NACA64A516