Similarly shaped airfoils to GOE 632
New! Bulk download of polars in Excel format: goe632.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. Eiffel 371 (Monge)
3. FX 79-W-151 A
4. EPPLER 344
5. NACA65-715 a=0.0
6. MRC-16
7. NACA65-615 a=0.2
8. NACA65-714 a=0.0
9. NACA64-715 a=0.0
10. NACA65-715 a=0.2
11. NACA65-614 a=0.2
12. NACA64-715 a=0.2
13. NACA4315
14. NACA64-615 a=0.2
15. GA 30A414
16. USA 45
17. AH 83-150 Q
18. AH 93-W-145
19. NACA63-715 a=0.0
20. NACA45014
21. NACA65-714 a=0.2