Similarly shaped airfoils to NACA63-209
New! Bulk download of polars in Excel format: NACA63-209.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. HQ 1.0/9
3. NACA63-209 a=0.8
4. NACA64-209 a=0.8
5. NACA63-209 a=0.6
6. NACA63-209 a=0.0
7. NACA63A209
8. NACA63-209 a=0.5
9. NACA64-209 a=0.6
10. NACA65-209
11. NACA63-209 a=0.2
12. NACA64-209 a=0.0
13. NACA64-209 a=0.5
14. NACA64-209 a=0.2
15. NACA64A209
16. NACA1409
17. NACA63-109 a=0.6
18. NACA63-109 a=0.8
19. NACA64-109 a=0.6
20. HQ 1.0/8
21. HN-456