Similarly shaped airfoils to NACA65-519 a=0.6
New! Bulk download of polars in Excel format: NACA65-519%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 40-419
3. GA 40A419
4. NACA65-519 a=0.8
5. NACA65-520 a=0.6
6. NACA65-518 a=0.6
7. GA 37A419
8. NACA65-619
9. NACA65-518 a=0.5
10. NACA65-520 a=0.5
11. GA 40-418
12. GA 40A418
13. NACA64A519
14. NACA64-519 a=0.6
15. GA 35A419
16. GA 37-419
17. GA 37A418
18. GA 40-420
19. GA 40A420
20. NACA64-519 a=0.5
21. NACA65-520 a=0.8