Similarly shaped airfoils to AH 79-K-143/18
New! Bulk download of polars in Excel format: ah79k143.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. NACA66-414 a=0.5
3. NACA65-415 a=0.5
4. GA 40A315
5. NACA66-414 a=0.6
6. GA 40-315
7. NACA65(2)-415 a=0.5
8. EPPLER 642
9. NACA66-514 a=0.2
10. AH 79-K-135/20 B
11. NACA65-415 a=0.6
12. AH 88-K-136/16
13. NACA65-515 a=0.2
14. NACA66-514 a=0.0
15. NACA66-415 a=0.5
16. NACA65-414 a=0.5
17. GA 37A315
18. GA 40A314
19. NACA 747A415
20. NACA65-515 a=0.0
21. GA 40-314