Similarly shaped airfoils to NACA64-418 a=0.2
New! Bulk download of polars in Excel format: NACA64-418%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. NACA63-418 a=0.2
3. NACA64-518 a=0.0
4. NACA63-418 a=0.0
5. NACA63-518 a=0.0
6. NACA64-318 a=0.5
7. NACA64-419 a=0.2
8. NACA64-417 a=0.2
9. GA 37-218
10. NACA63-318 a=0.5
11. NACA64-417 a=0.0
12. NACA64-318 a=0.6
13. NACA64-418 a=0.5
14. NACA64-519 a=0.0
15. GA 35-218
16. NACA63-417 a=0.2
17. NACA63-419 a=0.2
18. NACA65-418 a=0.2
19. NACA63-417 a=0.0
20. NACA64-318 a=0.2
21. NACA64-419 a=0.0