Similarly shaped airfoils to NACA64-314 a=0.0
New! Bulk download of polars in Excel format: NACA64-314%20a%3D0.0.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. NACA63-314 a=0.0
3. NACA63-314 a=0.2
4. NACA64-214 a=0.5
5. NACA63-214 a=0.5
6. NACA64-214 a=0.2
7. NACA64-214 a=0.6
8. NACA65-314 a=0.0
9. NACA63-214 a=0.2
10. NACA63-214 a=0.6
11. NACA65-314 a=0.2
12. GA 37-214
13. NACA64-315 a=0.0
14. NACA64-313 a=0.0
15. NACA64-315 a=0.2
16. NACA64-214 a=0.0
17. NACA63-313 a=0.0
18. GA 35-214
19. NACA63-315 a=0.0
20. NACA65-214 a=0.5
21. NACA64-313 a=0.2