Similarly shaped airfoils to GOE 116 (MVA MK.3)
New! Bulk download of polars in Excel format: goe116.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. MH 38 9.68%
3. DAE-51
4. NACA4410
5. GOE 602 MOD.
6. GOE 115 (MVA MK.2)
7. NACA63-610 a=0.6
8. NACA64-610 a=0.6
9. MH 116 9.84%
10. NACA63-610 a=0.5
11. GOE 117 (MVA MK.4)
12. NACA64-610 a=0.5
13. RAF 32 MOD
14. NACA63A610
15. NACA63-610 a=0.8
16. S4061-096-84
17. GOE 602
18. NACA63-609 a=0.6
19. NACA63A609
20. NACA64-610 a=0.8
21. NACA64-609 a=0.6