Similarly shaped airfoils to NACA64-609
New! Bulk download of polars in Excel format: NACA64-609.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. NACA64-509 a=0.8
3. NACA63-509 a=0.8
4. NACA65-609
5. NACA63A509
6. NACA64A509
7. NACA65-509 a=0.8
8. HQ 3.0/9
9. S7075 (9%)
10. EPPLER 64
11. NACA64-610
12. NACA65A509
13. NACA63-610
14. NACA64-509 a=0.6
15. NACA64-510 a=0.8
16. NACA63-509 a=0.6
17. HQ 3.0/8
18. NACA63-510 a=0.8
19. S4110
20. NACA64-709
21. NACA64-509