Similarly shaped airfoils to NACA63-519 a=0.6
New! Bulk download of polars in Excel format: NACA63-519%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. NACA64-519 a=0.6
3. GA 35-419
4. NACA64-519 a=0.5
5. NACA63-519 a=0.8
6. NACA63-520 a=0.6
7. NACA63-518 a=0.6
8. GA 37-419
9. NACA64-519 a=0.8
10. NACA63-518 a=0.5
11. NACA63-619
12. NACA63-520 a=0.5
13. NACA64-518 a=0.6
14. NACA64-520 a=0.6
15. GA 35-418
16. NACA64-518 a=0.5
17. NACA64-619
18. NACA64-520 a=0.5
19. NACA63-520 a=0.8
20. GA 35-420
21. GA 35-319