Similarly shaped airfoils to MILEY M06-13-128
New! Bulk download of polars in Excel format: miley.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. FX 77-W-121
3. EPPLER 639
4. NACA63-712 a=0.2
5. GOE 323 (HANSA-BRANDENBURG V.1)
6. NACA63-713 a=0.2
7. NACA64-712 a=0.2
8. EPPLER 598
9. RAF 33
10. AH 80-140
11. EPPLER 638
12. NACA63-711 a=0.2
13. NACA64-713 a=0.2
14. NACA63-712 a=0.0
15. GOE 321 (HANSA-BRANDENBURG III.1)
16. NACA64-711 a=0.2
17. SPICA 11.73% smoothed
18. NACA64-712 a=0.0
19. NACA63-713 a=0.0
20. NACA63-711 a=0.0
21. EPPLER 593