Similarly shaped airfoils to GOE 309 (MVA H.41)
New! Bulk download of polars in Excel format: goe309.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. GOE 316 (HANSA-BRANDENBURG IV.5)
3. NACA65-709 a=0.2
4. NACA66-709 a=0.2
5. GOE 286
6. USA 25
7. NACA64-709 a=0.2
8. GOE 188
9. GOE 310 (MVA H.42)
10. NACA65-709 a=0.0
11. AQUILA 9.3% smoothed
12. NACA66-709 a=0.0
13. GOE 308 (MVA H.40)
14. NACA63-709 a=0.2
15. GOE 385
16. NACA65-710 a=0.2
17. GOE 167 (V.KARMAN PROP.2)
18. NACA67-709 a=0.2
19. NACA64-710 a=0.2
20. GOE 287
21. NACA M14