Similarly shaped airfoils to GOE 392
New! Bulk download of polars in Excel format: goe392.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
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2. NACA63-710 a=0.6
3. NACA65-710 a=0.6
4. NACA64-710 a=0.8
5. NACA63A710
6. S4062-095-87
7. NACA63-710 a=0.8
8. NACA5510
9. NACA64A710
10. NACA64-710 a=0.5
11. NACA63-710 a=0.5
12. NACA65-710 a=0.8
13. GOE 477
14. GA 35A610
15. PSU 94-097 (AIAA 2001-2478)
16. GOE 450
17. NACA65-710 a=0.5
18. NACA64-711 a=0.6
19. NACA63-711 a=0.6
20. GA 37A610
21. NACA5509