Similarly shaped airfoils to GOE 723


New! Bulk download of polars in Excel format: goe723.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
Dynamic plotter New!
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.

1. GOE 682
2. EPPLER 393
3. GA 30-611
4. GA 30A611
5. EPPLER 214
6. NACA63-711 a=0.8
7. Joukowsky 12.00% thick 5.00% camber
8. FX 83-W-108
9. S4310
10. GA 35-611
11. GA 35-612
12. NACA63-712 a=0.8
13. NACA63-711 a=0.6
14. Joukowsky 12.00% thick 4.00% camber
15. NACA63-712 a=0.6
16. NACA63-611 a=0.6
17. SD7034
18. GA 30-610
19. GA 30A610
20. GOE 479
21. FX 63-110