Similarly shaped airfoils to FX 84-W-127
New! Bulk download of polars in Excel format: fx84w127.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. NACA63-613 a=0.5
3. CB3512
4. NACA64-613 a=0.6
5. NACA63-613 a=0.6
6. NM Classic 12 root
7. NACA4413
8. NACA64-513 a=0.6
9. NACA63-513 a=0.6
10. GA 35A413
11. NACA64-513 a=0.5
12. GA 37-413
13. GOE 796
14. NACA4412
15. HQ 3.5/13
16. AH 63-K-127/24
17. NACA63-513 a=0.5
18. GOE 693
19. CLARK-Y 11.7% smoothed
20. GA 35-413
21. GOE 623