Similarly shaped airfoils to NACA63-713 a=0.2
New! Bulk download of polars in Excel format: NACA63-713%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. NACA63-713 a=0.0
3. NACA64-713 a=0.0
4. NACA63-714 a=0.2
5. NACA63-712 a=0.2
6. NACA64-712 a=0.2
7. NACA64-714 a=0.2
8. NACA65-713 a=0.2
9. NACA63-712 a=0.0
10. NACA64-712 a=0.0
11. NACA63-613 a=0.2
12. NACA63-613 a=0.5
13. NACA65-713 a=0.0
14. NACA64-613 a=0.2
15. NACA63-714 a=0.0
16. NACA64-613 a=0.5
17. NACA65-712 a=0.2
18. NACA64-714 a=0.0
19. NACA65-712 a=0.0
20. AH 80-140
21. FX 05-H-126