Similarly shaped airfoils to GOE 318 (HANSA-BRANDENBURG VI.5)
New! Bulk download of polars in Excel format: goe318.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. NACA63-709 a=0.0
3. AQUILA 9.3% smoothed
4. NACA63-709 a=0.2
5. GOE 286
6. NACA64-709 a=0.0
7. GOE 315 (HANSA-BRANDENBURG III.5)
8. NACA64-709 a=0.2
9. NACA63-609 a=0.2
10. NACA63-710 a=0.0
11. NACA63-710 a=0.2
12. USA 22
13. NACA64-609 a=0.2
14. FAD21
15. NACA64-710 a=0.0
16. NACA64-710 a=0.2
17. NACA63-610 a=0.2
18. GOE 257
19. GOE 309 (MVA H.41)
20. NACA65-709 a=0.0
21. GOE 314 (HANSA-BRANDENBURG)