Similarly shaped airfoils to NACA64-509 a=0.5
New! Bulk download of polars in Excel format: NACA64-509%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. NACA64-509 a=0.6
3. NACA63-509 a=0.6
4. NACA65-509 a=0.5
5. NACA65-509 a=0.6
6. EPPLER 387
7. EPPLER 174
8. SD6080 (9.2%)
9. NACA64-510 a=0.5
10. NACA63-510 a=0.5
11. GA 37-410
12. MID 321a
13. NACA64-510 a=0.6
14. EPPLER 176
15. NACA63-510 a=0.6
16. GA 35-410
17. S3025 9.38%
18. NACA64-609 a=0.0
19. NACA64-609 a=0.2
20. S4053
21. NACA63-609 a=0.2