Similarly shaped airfoils to MH 61 10.26%
New! Bulk download of polars in Excel format: mh61.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. NACA63-210 a=0.2
3. AZcombat1
4. FAD04
5. NACA63-210 a=0.5
6. NACA63-210 a=0.0
7. NACA63-310 a=0.0
8. HM10011
9. MH 60 10.08%
10. NACA64-210 a=0.2
11. MH 45 9.85%
12. HM50
13. NACA63-210 a=0.6
14. Sipkill 1.7/10
15. NACA64-210 a=0.5
16. NACA64-210 a=0.0
17. NACA63-211 a=0.2
18. NACA64-310 a=0.0
19. Horten 10.00% thick 2.00% camber
20. EH 2.0/10
21. NACA63-311 a=0.0