Similarly shaped airfoils to DAE-51
New! Bulk download of polars in Excel format: dae51.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. MH 38 9.68%
3. MH 116 9.84%
4. PSU 94-097 (AIAA 2001-2478)
5. NACA63-610 a=0.6
6. NACA4409
7. EPPLER 392
8. SD7032-099-88
9. SD7043 (9.1%)
10. NACA64-610 a=0.6
11. S4062-095-87
12. NACA63-609 a=0.6
13. GOE 116 (MVA MK.3)
14. NACA64-609 a=0.6
15. NACA63-610 a=0.8
16. GOE 117 (MVA MK.4)
17. HQ 3.5/9
18. NACA63-610 a=0.5
19. GA 35-610
20. GOE 596
21. HQ 3.5/10