Similarly shaped airfoils to NACA64-518 a=0.8
New! Bulk download of polars in Excel format: NACA64-518%20a%3D0.8.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. NACA63-518 a=0.8
3. NACA63-618
4. NACA64-518 a=0.6
5. NACA64-519 a=0.8
6. NACA64-517 a=0.8
7. NACA63-518 a=0.6
8. NACA64-718
9. NACA64-619
10. NACA63A517
11. NACA64-617
12. NACA63A518
13. NACA63-517 a=0.8
14. NACA63-519 a=0.8
15. NACA65-518 a=0.8
16. NACA63-617
17. NACA63-619
18. NACA65-618
19. GA 37-418
20. NACA64-518
21. NACA63-718