Similarly shaped airfoils to NACA65-317 a=0.8
New! Bulk download of polars in Excel format: NACA65-317%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. NACA65-317 a=0.6
3. NACA64A317
4. GA 40-217
5. GA 40A217
6. NACA65-317
7. NACA65-317 a=0.5
8. NACA63A317
9. GA 37A217
10. NACA65-318 a=0.8
11. NACA65-316 a=0.8
12. NACA64-317 a=0.8
13. NACA65-418
14. NACA65A317
15. NACA64-417
16. NACA64A316
17. NACA65-416
18. NACA65-316 a=0.6
19. NACA65-318 a=0.6
20. GA 35A217
21. NACA65A316