Similarly shaped airfoils to NACA63-513 a=0.6
New! Bulk download of polars in Excel format: NACA63-513%20a%3D0.6.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. NACA63-513 a=0.5
3. GA 35-413
4. NACA64-513 a=0.5
5. GA 37-413
6. NACA63-513 a=0.8
7. NACA64-513 a=0.8
8. GA 35A413
9. NACA63-514 a=0.6
10. NACA63-512 a=0.6
11. S4233-136-84
12. MS3/13GPV
13. NACA64-512 a=0.6
14. NACA64-514 a=0.6
15. NACA63-613
16. GA 35-414
17. FX 84-W-127
18. NACA63-512 a=0.5
19. NACA63-514 a=0.5
20. HQ 3.0/13
21. NACA65-513 a=0.6