Similarly shaped airfoils to NACA65-514 a=0.0
New! Bulk download of polars in Excel format: NACA65-514%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. NACA65-414 a=0.2
3. NACA64-514 a=0.0
4. NACA64-514 a=0.2
5. NACA65-414 a=0.5
6. NACA65-515 a=0.0
7. NACA65-513 a=0.0
8. GA 40-314
9. GA 40A314
10. NACA65-515 a=0.2
11. NACA65-414 a=0.0
12. GA 37A314
13. NACA65-614 a=0.0
14. NACA64-515 a=0.0
15. NACA64-414 a=0.2
16. NACA64-515 a=0.2
17. NACA65-413 a=0.2
18. NACA65-513 a=0.2
19. NACA63-514 a=0.0
20. AH 81-131
21. NACA65-415 a=0.2