Similarly shaped airfoils to NACA65-517 a=0.5
New! Bulk download of polars in Excel format: NACA65-517%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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. GA 40-417
3. GA 40A417
4. GA 37A417
5. NACA65-518 a=0.5
6. NACA65-516 a=0.5
7. NACA64-517 a=0.5
8. GA 35A417
9. NACA65-518 a=0.6
10. NACA65-516 a=0.6
11. NACA64-517 a=0.6
12. GA 37-417
13. NACA65-617 a=0.2
14. GA 40-416
15. GA 40A416
16. GA 40-418
17. GA 40A418
18. GA 37A416
19. NACA65-617 a=0.0
20. NACA65-517 a=0.8
21. NACA64-518 a=0.5