Similarly shaped airfoils to NACA64-315 a=0.8
New! Bulk download of polars in Excel format: NACA64-315%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. NACA63-315 a=0.8
3. NACA64-315 a=0.6
4. NACA63-415
5. NACA63-315 a=0.6
6. GA 37-215
7. NACA64-315
8. NACA64-315 a=0.5
9. GA 35-215
10. NACA63-315
11. NACA63A315
12. NACA63-315 a=0.5
13. NACA65-315 a=0.8
14. NACA63A314
15. NACA64A315
16. NACA64-316 a=0.8
17. NACA64-314 a=0.8
18. NACA64-416
19. NACA65-415
20. NACA65-315 a=0.6
21. NACA63-314 a=0.8