Similarly shaped airfoils to NACA63-410 a=0.2
New! Bulk download of polars in Excel format: NACA63-410%20a%3D0.2.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. NACA63-410 a=0.0
3. NACA64-410 a=0.0
4. NACA63-510 a=0.0
5. GA 35-310
6. GA 37-310
7. NACA64-510 a=0.0
8. NACA65-410 a=0.2
9. NACA65-410 a=0.0
10. FX 84-W-097
11. S3014-095-85
12. S3016-095-87
13. GA 35A310
14. NACA63-411 a=0.2
15. NACA63-409 a=0.2
16. TL54
17. TT54
18. NACA63-310 a=0.5
19. NACA63-410 a=0.5
20. NACA64-409 a=0.2
21. NACA64-411 a=0.2