Similarly shaped airfoils to NACA63-512 a=0.5
New! Bulk download of polars in Excel format: NACA63-512%20a%3D0.5.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 35-412
3. NACA63-512 a=0.6
4. GA 37-412
5. NACA64-512 a=0.6
6. GA 35A412
7. EPPLER 195
8. NACA63-513 a=0.5
9. NACA63-511 a=0.5
10. GA 37A412
11. GA 35-413
12. GA 40-412
13. NACA65-512 a=0.5
14. NACA64-511 a=0.5
15. BOEING-VERTOL VR-5
16. NACA64-513 a=0.5
17. GA 40A412
18. GA 37-413
19. GA 30-411
20. NACA63-513 a=0.6
21. GA 35A411