Similarly shaped airfoils to NACA65-415 a=0.2
New! Bulk download of polars in Excel format: NACA65-415%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. NACA65-515 a=0.0
3. NACA 747A315
4. NACA64-415 a=0.2
5. NACA65-315 a=0.5
6. NACA65-416 a=0.2
7. NACA65-414 a=0.2
8. GA 40-315
9. NACA65-415 a=0.5
10. NACA64-515 a=0.0
11. GA 40A315
12. NACA65-414 a=0.0
13. NACA64-415 a=0.0
14. MB253515 15.0% smoothed
15. NACA65-315 a=0.6
16. NACA65-416 a=0.0
17. GA 40-215
18. GA 40A215
19. NACA65-516 a=0.0
20. NACA64-416 a=0.2
21. GA 37A315