Similarly shaped airfoils to NACA64-415 a=0.8
New! Bulk download of polars in Excel format: NACA64-415%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. NACA63-415 a=0.8
3. NACA63-515
4. NACA64(2)-415
5. NACA64-415 a=0.6
6. NACA63-415 a=0.6
7. NACA63A415
8. GA 37-315
9. NACA65-415 a=0.8
10. NACA63A414
11. GA 35-315
12. NACA64-415
13. NACA64A415
14. NACA64-416 a=0.8
15. NACA64-415 a=0.5
16. NACA64-414 a=0.8
17. NACA65-515
18. NACA64-516
19. NACA65(2)-415
20. NACA63-415
21. NACA64-514