Similarly shaped airfoils to NACA63-420 a=0.8
New! Bulk download of polars in Excel format: NACA63-420%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. NACA64-420 a=0.8
3. NACA64-520
4. NACA63-420 a=0.6
5. NACA64-420 a=0.6
6. NACA63-420
7. NACA63-419 a=0.8
8. NACA63-420 a=0.5
9. GA 35-320
10. NACA63-519
11. NACA64-419 a=0.8
12. NACA64-519
13. NACA64-420 a=0.5
14. NACA63-419 a=0.6
15. NACA64-420
16. NACA63-620
17. NACA63(4)-421
18. NACA64-620
19. NACA63-320 a=0.8
20. GA 37-320
21. NACA63-320 a=0.6