Similarly shaped airfoils to NACA64-413
New! Bulk download of polars in Excel format: NACA64-413.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. NACA64-313 a=0.8
3. NACA63-313 a=0.8
4. NACA64-313 a=0.6
5. NACA65-413
6. NACA63-313 a=0.6
7. NACA63A313
8. NACA65-313 a=0.8
9. RAF 31
10. NACA64-313 a=0.5
11. GA 37-213
12. NACA64A313
13. EM CY 1016 2012
14. NACA63-313 a=0.5
15. NACA64-414
16. NACA64-412
17. HQ 2.0/12
18. NACA64-413 a=0.8
19. NACA65-313 a=0.6
20. NACA63A312
21. GA 35-213