Similarly shaped airfoils to NACA64-520 a=0.8
New! Bulk download of polars in Excel format: NACA64-520%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. NACA63-520 a=0.8
3. NACA63-620
4. NACA64-520 a=0.6
5. NACA64-519 a=0.8
6. NACA64-720
7. NACA64-619
8. NACA63-520 a=0.6
9. NACA63-519 a=0.8
10. NACA63A519
11. NACA63-619
12. NACA64-520
13. NACA63A520
14. GA 37-320
15. NACA64-520 a=0.5
16. NACA63-520
17. NACA64-420 a=0.8
18. NACA65-520 a=0.8
19. NACA63-720
20. NACA64-620 a=0.8
21. GA 35-320