Similarly shaped airfoils to NACA65-316 a=0.0
New! Bulk download of polars in Excel format: NACA65-316%20a%3D0.0.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. NACA65-216 a=0.5
3. NACA65-216 a=0.2
4. NACA65-216 a=0.6
5. EPPLER 502
6. NACA64-316 a=0.0
7. NACA65-317 a=0.0
8. NACA65-315 a=0.0
9. NACA64-316 a=0.2
10. GA 40-216
11. NACA65-317 a=0.2
12. GA 40A216
13. NACA65-216 a=0.0
14. NACA65-315 a=0.2
15. NACA65-416 a=0.0
16. NACA65-216 a=0.8
17. NACA65-316 a=0.5
18. NACA65-316
19. NACA65-215 a=0.5
20. GA 37A216
21. NACA65-217 a=0.5