Similarly shaped airfoils to NACA65-417 a=0.5
New! Bulk download of polars in Excel format: NACA65-417%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 40-317
3. GA 40A317
4. GA 37A317
5. NACA65-517 a=0.0
6. NACA65-417 a=0.8
7. NACA65-418 a=0.5
8. NACA65-416 a=0.5
9. NACA65-517 a=0.2
10. GA 35A317
11. NACA64-417 a=0.5
12. NACA65-418 a=0.6
13. NACA65-417 a=0.2
14. NACA65-416 a=0.6
15. GA 37-317
16. NACA64-417 a=0.6
17. NACA65-517
18. GA 40-316
19. GA 40A316
20. GA 40-318
21. GA 40A318