Similarly shaped airfoils to NACA64-609 a=0.8
New! Bulk download of polars in Excel format: NACA64-609%20a%3D0.8.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. NACA63A609
3. NACA65-609 a=0.8
4. NACA64-709
5. NACA64A609
6. NACA63-709
7. NACA65-709
8. HQ 3.5/9
9. NACA65A609
10. NACA64-610 a=0.8
11. NACA63-610 a=0.8
12. NACA64-609 a=0.6
13. NACA63-609 a=0.6
14. NACA64-710
15. NACA65-609 a=0.6
16. DAE-51
17. NACA63-710
18. NACA63A709
19. NACA65-610 a=0.8
20. GOE 602 MOD.
21. HQ 3.5/8