Similarly shaped airfoils to NACA67-519 a=0.6
New! Bulk download of polars in Excel format: NACA67-519%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. NACA67-519 a=0.8
3. NACA67A519
4. NACA67-619
5. NACA67-520 a=0.6
6. NACA67-518 a=0.6
7. NACA67-518 a=0.5
8. NACA67-520 a=0.5
9. NACA67-719
10. NACA67-619 a=0.5
11. NACA67A619
12. NACA67-419 a=0.6
13. NACA67-619 a=0.6
14. NACA67-520 a=0.8
15. NACA67-518 a=0.8
16. NACA67A518
17. NACA67A520
18. NACA67-619 a=0.8
19. NACA67-620
20. NACA67-419 a=0.5
21. NACA67-618