Similarly shaped airfoils to NACA63-515 a=0.2
New! Bulk download of polars in Excel format: NACA63-515%20a%3D0.2.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. NACA63-515 a=0.0
3. NACA63-615 a=0.0
4. NACA64-615 a=0.0
5. NACA64-515 a=0.0
6. NACA63-516 a=0.2
7. NACA63-514 a=0.2
8. NACA63-415 a=0.5
9. NACA64-514 a=0.2
10. NACA64-516 a=0.2
11. NACA63-514 a=0.0
12. NACA63-616 a=0.0
13. NACA64-415 a=0.5
14. GA 35-315
15. NACA64-514 a=0.0
16. NACA64-616 a=0.0
17. NACA63-516 a=0.0
18. GA 37-315
19. NACA63-415 a=0.2
20. NACA63-614 a=0.0
21. NACA63-615 a=0.2