Similarly shaped airfoils to GOE 114 (MVA MK.1)
New! Bulk download of polars in Excel format: goe114.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. NACA63A509
3. NACA63-509 a=0.8
4. NACA64A509
5. NACA64-509 a=0.8
6. OAF102
7. EPPLER 64
8. NACA63-510 a=0.8
9. NACA63-609
10. NACA64-510 a=0.8
11. NACA64-609
12. NACA63-610
13. NACA63A510
14. NACA64-610
15. NACA65-509 a=0.8
16. S7075 (9%)
17. NACA63-509 a=0.6
18. NACA64A510
19. MH 122 9.32%
20. NACA65-609
21. NACA64-509 a=0.6