Similarly shaped airfoils to Fage & Collins 1
New! Bulk download of polars in Excel format: fg1.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. Fage & Collins 2
3. FX 69-H-083
4. HL75-K-3
5. NACA65-509 a=0.0
6. Coanda 3
7. NACA64-509 a=0.0
8. NACA63-509 a=0.0
9. USA 51
10. NACA65-409 a=0.2
11. GOE 515
12. NACA66-509 a=0.0
13. NACA65-509 a=0.2
14. GOE 795 smoothed
15. NACA35009
16. NACA64-409 a=0.2
17. SD2083 (9.0%)
18. GOE 564
19. NACA64-509 a=0.2
20. GOE 795
21. RK40