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
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. 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