Similarly shaped airfoils to MJZ1211
New! Bulk download of polars in Excel format: MJZ1211.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. NPL 9627
3. NACA23012
4. NPL 9626
5. NACA63-212 a=0.0
6. Horten 11.00% thick 1.00% camber
7. Horten 12.00% thick 1.00% camber
8. NACA1412
9. GOE 766
10. NPL 9660
11. MH 106 13.07%
12. ONERA NACA CAMBRE
13. NPL 9615
14. NACA63-212 a=0.2
15. NACA22012
16. NACA64-212 a=0.0
17. Horten 12.00% thick 2.00% camber
18. HQ 1.0/12
19. NACA63-213 a=0.0
20. NACA23112
21. NACA63-112 a=0.5