Similarly shaped airfoils to NACA63-313
New! Bulk download of polars in Excel format: NACA63-313.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
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2. NACA63-213 a=0.8
3. NACA63-213 a=0.6
4. NACA64-213 a=0.8
5. NACA63-313 a=0.8
6. NACA64-213 a=0.6
7. GA 35-213
8. NACA63-213 a=0.5
9. NACA64-313 a=0.8
10. GA 37-213
11. HQ 1.5/12
12. NACA64-213 a=0.5
13. NACA63-314
14. NACA63-312
15. NACA63-313 a=0.6
16. NACA64-312
17. NACA64-314
18. NACA64-313 a=0.6
19. NACA63-313 a=0.5
20. NACA63-213
21. NACA63-413