Similarly shaped airfoils to FX 63-100
New! Bulk download of polars in Excel format: fx63100.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. Joukowsky 10.00% thick 5.00% camber
3. NACA63-710 a=0.8
4. GOE 496
5. NACA63-709 a=0.8
6. S4062-095-87
7. NACA64-710 a=0.8
8. Joukowsky 9.00% thick 5.00% camber
9. Joukowsky 11.00% thick 5.00% camber
10. EPPLER 66
11. NACA5509
12. NACA64-709 a=0.8
13. PSU 94-097 (AIAA 2001-2478)
14. EPPLER 392
15. SD7043 (9.1%)
16. NACA63A709
17. EPPLER 216
18. MID 107
19. MH 116 9.84%
20. SD7032-099-88
21. NACA5510