Similarly shaped airfoils to NACA63-313 a=0.8
New! Bulk download of polars in Excel format: NACA63-313%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
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2. NACA63-413
3. NACA63-313 a=0.6
4. NACA64-413
5. NACA64-313 a=0.6
6. GA 35-213
7. NACA63-313 a=0.5
8. NACA63-313
9. GA 37-213
10. NACA64-313 a=0.5
11. NACA64-313
12. NACA63A313
13. RAF 31
14. NACA63-314 a=0.8
15. NACA63-312 a=0.8
16. HQ 1.5/12
17. NACA64-312 a=0.8
18. NACA63-414
19. NACA64-314 a=0.8
20. NACA63A312
21. HQ 2.0/12