Similarly shaped airfoils to AH 93-K-130/15
New! Bulk download of polars in Excel format: ah93k130.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. AH 93-K-132/15
3. NACA66-513 a=0.5
4. NACA66-613 a=0.2
5. AH 79-K-132/20
6. NACA66-613 a=0.0
7. NACA65-614 a=0.2
8. NACA65-514 a=0.5
9. NACA66-713 a=0.0
10. NACA66-513 a=0.6
11. NACA66-614 a=0.2
12. NACA66-514 a=0.5
13. AH 80-129
14. NACA65-513 a=0.5
15. NACA65-613 a=0.2
16. AH 88-K-136/16
17. AH 79-K-135/20 B
18. NACA65-614 a=0.0
19. NACA65-714 a=0.0
20. NACA66-513 a=0.2
21. NACA65-613 a=0.0