Similarly shaped airfoils to FX 69-H-083
New! Bulk download of polars in Excel format: fx69h083.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (4) | 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. NACA65-409 a=0.2
3. NACA64-409 a=0.0
4. NACA64-409 a=0.2
5. RK40
6. NACA63-409 a=0.2
7. NACA63-409 a=0.0
8. DP2.06/8.67_DS
9. DP2.05/8.65_DS
10. NACA65-309 a=0.5
11. NACA66-409 a=0.0
12. NACA64-309 a=0.5
13. NACA66-409 a=0.2
14. EPPLER 180
15. GOE 795 smoothed
16. GOE 795
17. NACA65-309 a=0.2
18. GOE 566
19. BOEING 707 .99 SPAN
20. NACA63-309 a=0.5
21. B-29 TIP