Similarly shaped airfoils to ONERA OA213
New! Bulk download of polars in Excel format: oa213.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. NACA63-613 a=0.0
3. EPPLER 338
4. NACA45013.5
5. NACA45012
6. NACA64-613 a=0.0
7. HS 3.4.12b
8. NACA44012
9. EPPLER 329
10. NACA63-614 a=0.0
11. NACA35013
12. HL80-133
13. NACA63-513 a=0.2
14. NACA64-614 a=0.0
15. NACA64-513 a=0.2
16. HS 3.5/12
17. NACA63-613 a=0.2
18. NACA35012
19. BOEING VERTOL V43012-1.58
20. EPPLER 637
21. NACA64-613 a=0.2