Similarly shaped airfoils to AH 81-131
New! Bulk download of polars in Excel format: ah81131.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
Dynamic plotter New!
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. RONCZ LOW DRAG FLYING WING
3. NACA65-413 a=0.2
4. NACA65-513 a=0.2
5. NACA65-514 a=0.0
6. NACA65-413 a=0.5
7. NACA65-514 a=0.2
8. NACA66-513 a=0.0
9. NACA64-513 a=0.0
10. AH 88-K-136/16
11. NACA65-414 a=0.2
12. NACA65-413 a=0.0
13. NACA64-514 a=0.0
14. NACA66-413 a=0.2
15. NACA65-414 a=0.5
16. NACA64-513 a=0.2
17. EPPLER 231
18. GA 40-313
19. GA 40A313
20. NACA64-514 a=0.2
21. NACA66-513 a=0.2