Similarly shaped airfoils to NACA64-610 a=0.8
New! Bulk download of polars in Excel format: NACA64-610%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. NACA64-710
3. NACA63A610
4. NACA65-610 a=0.8
5. NACA63-710
6. NACA64A610
7. NACA65-710
8. RAF 32 MOD
9. NACA63A609
10. MH 116 9.84%
11. HQ 3.5/10
12. NACA64A609
13. NACA64-611 a=0.8
14. NACA64-609 a=0.8
15. NACA65-609 a=0.8
16. NACA63-609 a=0.8
17. NACA64-610 a=0.6
18. NACA63-611 a=0.8
19. NACA63-610 a=0.6
20. NACA65A610
21. GOE 602 MOD.