Similarly shaped airfoils to NACA63-021
New! Bulk download of polars in Excel format: NACA63-021.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. GA 35-020
3. GA 37-020
4. NACA63-120 a=0.0
5. NACA63-120
6. NACA63-120 a=0.2
7. NACA64-120 a=0.0
8. NACA64-120
9. NACA64-120 a=0.2
10. NACA63-120 a=0.8
11. NACA63-120 a=0.5
12. NACA63-120 a=0.6
13. NACA64-120 a=0.8
14. NACA64-120 a=0.5
15. NACA64-120 a=0.6
16. GA 35A020
17. DU06-W-200_VAWT
18. Horten 20.00% thick 0.00% camber
19. NACA63-221
20. NACA64-221
21. GA 30-020