Similarly shaped airfoils to AH 80-140
New! Bulk download of polars in Excel format: ah80140.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
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. GOE 633
3. NACA63-713 a=0.2
4. NACA63-714 a=0.0
5. NACA63-713 a=0.0
6. NACA64-714 a=0.2
7. NACA63-614 a=0.2
8. NACA63-613 a=0.2
9. RAF 33
10. NACA64-713 a=0.2
11. NACA64-714 a=0.0
12. NACA64-713 a=0.0
13. FX 77-W-153
14. USA 45
15. NM Spatz 13%
16. FX 05-H-126
17. MH 82 13.31%
18. NACA63-715 a=0.2
19. TsAGI R3A-15
20. NM Spatz 14%
21. EPPLER 639