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
Dynamic plotter New!
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.

1. NACA M8 (NACA-TR-221)
2. GOE 257
3. GOE 316 (HANSA-BRANDENBURG IV.5)
4. NACA65-709 a=0.2
5. NACA66-709 a=0.2
6. GOE 286
7. USA 25
8. NACA64-709 a=0.2
9. GOE 188
10. GOE 310 (MVA H.42)
11. NACA65-709 a=0.0
12. AQUILA 9.3% smoothed
13. NACA66-709 a=0.0
14. GOE 308 (MVA H.40)
15. NACA63-709 a=0.2
16. GOE 385
17. NACA65-710 a=0.2
18. GOE 167 (V.KARMAN PROP.2)
19. NACA67-709 a=0.2
20. NACA64-710 a=0.2
21. NACA M17 (NACA-TR-221)