Similarly shaped airfoils to FX 71-L-150/30
New! Bulk download of polars in Excel format: fx711530.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 71-L-150/20
3. NACA63-015
4. GA 35-015
5. NACA64-015
6. GA 37-015
7. NACA63-115 a=0.0
8. EPPLER 477
9. NACA63-115
10. GA 35-014
11. NACA63-115 a=0.2
12. GA 35-016
13. FX LIII-142 K 25
14. S8035 (14%)
15. NACA64-115 a=0.0
16. Horten 14.00% thick 0.00% camber
17. NACA63-115 a=0.8
18. NACA64-115
19. GA 37-014
20. NACA63-115 a=0.5
21. NACA63-115 a=0.6