Similarly shaped airfoils to NACA66-513 a=0.5
New! Bulk download of polars in Excel format: NACA66-513%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
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2. NACA66-514 a=0.5
3. NACA66-512 a=0.5
4. AH 93-K-130/15
5. AH 93-K-132/15
6. NACA67-513 a=0.5
7. NACA66-514 a=0.6
8. NACA67-512 a=0.5
9. NACA66-613 a=0.2
10. NACA66-512 a=0.6
11. NACA67-513 a=0.6
12. NACA66-613 a=0.0
13. AH 93-K-131/15
14. NACA66-513 a=0.8
15. AH 79-K-132/20
16. NACA67-512 a=0.6
17. NACA65-513 a=0.5
18. NACA66A513
19. NACA66-513 a=0.2
20. NACA65-514 a=0.5
21. NACA65-513 a=0.6