Similarly shaped airfoils to NACA64-021
New! Bulk download of polars in Excel format: NACA64-021.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (2) | 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. GA 37-020
3. GA 35-020
4. NACA64-120 a=0.0
5. NACA64-120
6. GA 35A020
7. NACA64-120 a=0.2
8. NACA65-021
9. NACA63-120 a=0.0
10. NACA63-120
11. NACA64-120 a=0.8
12. NACA64-120 a=0.5
13. NACA63-120 a=0.2
14. NACA64-120 a=0.6
15. GA 37A020
16. GA 40-020
17. NACA63-120 a=0.8
18. NACA63-120 a=0.5
19. NACA63-120 a=0.6
20. GA 40A020
21. NACA63A120