Similarly shaped airfoils to NACA64-410 a=0.6
New! Bulk download of polars in Excel format: NACA64-410%20a%3D0.6.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. NACA64-410 a=0.5
3. NACA63-410 a=0.5
4. NACA65-410 a=0.6
5. GA 37-310
6. NACA65-410 a=0.5
7. NACA64-410 a=0.8
8. NACA63-410 a=0.8
9. EPPLER EB380
10. GA 35-310
11. GA 35A310
12. GA 40-310
13. FX 84-W-097
14. GA 40A310
15. GA 37A310
16. NACA64-510
17. NACA63-510
18. HQ 2.5/10
19. SD2083 (9.0%)
20. NACA63A410
21. NACA65-410 a=0.8