Similarly shaped airfoils to NACA63-213 a=0.8
New! Bulk download of polars in Excel format: NACA63-213%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. NACA64-213 a=0.8
3. NACA63-213 a=0.5
4. NACA63-213
5. NACA64-213 a=0.6
6. NACA64-213 a=0.5
7. NACA64-213
8. NACA63-313
9. NACA64-313
10. NACA63-213 a=0.2
11. NACA63A213
12. HQ 1.0/12
13. NACA64-213 a=0.2
14. NACA63-213 a=0.0
15. NACA63-214 a=0.8
16. NACA63-212 a=0.8
17. NACA64-213 a=0.0
18. NACA63-214 a=0.6
19. NACA63-212 a=0.6
20. NACA64-212 a=0.8
21. NACA64-214 a=0.8