Similarly shaped airfoils to NACA65-313 a=0.0
New! Bulk download of polars in Excel format: NACA65-313%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. NACA65-213 a=0.5
3. NACA64-313 a=0.0
4. GA 40-213
5. GA 40A213
6. NACA64-313 a=0.2
7. NACA65-213 a=0.6
8. NACA65-213 a=0.2
9. Europa Dykins 12%
10. GA 37A213
11. NACA65-314 a=0.0
12. NACA65-312 a=0.0
13. HSNLF(1)-0213
14. NACA65-314 a=0.2
15. GA 35A213
16. NACA65-313 a=0.5
17. NACA65-312 a=0.2
18. NACA65-213 a=0.0
19. NACA64-213 a=0.5
20. NACA64-314 a=0.0
21. NACA64-314 a=0.2