Similarly shaped airfoils to EPPLER STE 871-514
New! Bulk download of polars in Excel format: ste87151.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (1) | 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. NACA67-314 a=0.8
3. NACA67A314
4. NACA66-314 a=0.8
5. NACA66A314
6. NACA67A414
7. NACA66-415
8. NACA67-414 a=0.8
9. NACA66A414
10. NACA66(2)-415
11. NACA67-314 a=0.6
12. NACA66-315 a=0.8
13. NACA66-314 a=0.6
14. NACA66A315
15. NACA67-313 a=0.8
16. NACA66-414 a=0.8
17. NACA67A313
18. NACA66A415
19. NACA66-514
20. NACA67-314 a=0.5
21. NACA66-415 a=0.8