Similarly shaped airfoils to NACA65-516 a=0.6
New! Bulk download of polars in Excel format: NACA65-516%20a%3D0.6.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 40-416
3. GA 40A416
4. GA 37A416
5. NACA65-516 a=0.8
6. NACA64-516 a=0.6
7. NACA65-517 a=0.6
8. NACA65-515 a=0.6
9. GA 35A416
10. NACA65-616
11. NACA65-515 a=0.5
12. GA 37-416
13. cristal_cb85_15_7
14. NACA64-516 a=0.5
15. NACA65-517 a=0.5
16. NACA64A516
17. GA 40-417
18. GA 40A415
19. GA 40-415
20. GA 40A417
21. GA 37A415