Similarly shaped airfoils to LOCKHEED C-5A BL1256
New! Bulk download of polars in Excel format: c5e.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. NACA63A211
3. NACA64A211
4. NACA65-211 a=0.6
5. NACA65-211 a=0.5
6. NACA65-211 a=0.8
7. NACA64-211 a=0.6
8. NACA64-211 a=0.5
9. HQ 1.5/11
10. NACA64-211 a=0.8
11. NACA65-311
12. NACA64-311
13. BOEING 737 OUTBOARD
14. GA 35A211
15. GA 37A211
16. RG 14 10%
17. NACA65A211
18. NACA65-211 a=0.2
19. NACA63-211 a=0.6
20. NACA63-211 a=0.5
21. NACA63-211 a=0.8