Similarly shaped airfoils to NACA64-309 a=0.8
New! Bulk download of polars in Excel format: NACA64-309%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. NACA63A309
3. NACA64-409
4. NACA64-309 a=0.6
5. NACA65-309 a=0.8
6. NACA63-409
7. NACA64A309
8. NACA63-309 a=0.6
9. HQ-2.0/9 9.0% smoothed
10. S2048
11. HQ 2.0/9
12. NACA65-409
13. NACA64-309 a=0.5
14. NACA65-309 a=0.6
15. HN-184
16. NACA64-309
17. NACA63-309 a=0.5
18. HN-163
19. HN-450S
20. NACA63-309
21. RG-15 8.9%