Similarly shaped airfoils to NACA63-509 a=0.5
New! Bulk download of polars in Excel format: NACA63-509%20a%3D0.5.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. NACA63-509 a=0.6
3. NACA64-509 a=0.6
4. EPPLER 387
5. EPPLER 174
6. SD6080 (9.2%)
7. NACA65-509 a=0.5
8. NACA65-509 a=0.6
9. EPPLER 176
10. NACA63-510 a=0.5
11. MID 321a
12. NACA64-510 a=0.5
13. GA 35-410
14. S3025 9.38%
15. GA 37-410
16. NACA63-510 a=0.6
17. S4061-096-84
18. MID 322
19. NACA64-510 a=0.6
20. S4053
21. NACA63-609 a=0.0