Similarly shaped airfoils to AH 82-150 F
New! Bulk download of polars in Excel format: ah82150f.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. NACA66-715
3. NACA66A615
4. NACA66-615 a=0.5
5. NACA66-515 a=0.6
6. NACA66-615 a=0.8
7. NACA66-616 a=0.6
8. NACA67-615 a=0.6
9. NACA66-515 a=0.5
10. NACA66-716
11. NACA66A616
12. NACA66-616 a=0.5
13. NACA67-715
14. NACA67-615 a=0.5
15. NACA67A615
16. NACA66-616 a=0.8
17. NACA67-615 a=0.8
18. AH 94-156
19. NACA66-516 a=0.6
20. NACA67-515 a=0.6
21. NACA66-515 a=0.8