Similarly shaped airfoils to GOE 14K
New! Bulk download of polars in Excel format: goe14k.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
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.
2. NACA67-412 a=0.8
3. NACA67A412
4. NACA67A413
5. NACA67-413 a=0.6
6. NACA67-412 a=0.6
7. NACA67A513
8. NACA67-613
9. NACA67A512
10. NACA67-513 a=0.8
11. NACA67-612
12. NACA67-512 a=0.8
13. NACA67-412 a=0.5
14. NACA67-413 a=0.5
15. NACA66-413 a=0.8
16. NACA66-513
17. NACA66A413
18. NACA67-414 a=0.8
19. NACA67-312 a=0.8
20. NACA67-411 a=0.8
21. NACA67A414