Similarly shaped airfoils to NACA64(4)-221
New! Bulk download of polars in Excel format: NACA64%284%29-221.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. NACA64-221
3. NACA63-221
4. NACA64-320
5. NACA64-220 a=0.8
6. NACA64-421
7. NACA64-220 a=0.6
8. NACA63-320
9. NACA63-220 a=0.8
10. NACA63A220
11. NACA64-220
12. NACA64-220 a=0.5
13. NACA65(4)-221
14. NACA63-220 a=0.6
15. NACA63-220
16. NACA63-220 a=0.5
17. NACA64-320 a=0.8
18. NACA63-421
19. NACA65-220 a=0.8
20. NACA65-221
21. NACA65-320