Similarly shaped airfoils to NACA63-609
New! Bulk download of polars in Excel format: NACA63-609.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. NACA63-509 a=0.8
3. NACA64-509 a=0.8
4. HQ 3.0/9
5. NACA63A509
6. NACA65-609
7. NACA64A509
8. EPPLER 64
9. NACA65-509 a=0.8
10. S7075 (9%)
11. S4110
12. NACA63-610
13. NACA64-610
14. HQ 3.0/8
15. NACA63-509 a=0.6
16. NACA63-510 a=0.8
17. NACA64-509 a=0.6
18. NACA64-510 a=0.8
19. HN-354OC
20. NACA63-509
21. NACA63-709