Similarly shaped airfoils to NACA5510
New! Bulk download of polars in Excel format: NACA5510.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. NACA5509
3. NACA63-710 a=0.8
4. NACA64A710
5. NACA64-710 a=0.8
6. EPPLER 66
7. NACA63-711 a=0.8
8. GOE 496
9. GOE 392
10. NACA64-711 a=0.8
11. S4062-095-87
12. NACA65-710 a=0.8
13. NACA63A711
14. AF140k
15. MH 116 9.84%
16. EPPLER 216
17. NACA65A710
18. NACA64A711
19. NACA63A709
20. Joukowsky 11.00% thick 5.00% camber
21. NACA63-710 a=0.6