Similarly shaped airfoils to KC-135 BL200.76
New! Bulk download of polars in Excel format: kc135c.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. NACA65-211 a=0.0
3. BOEING 737 OUTBOARD
4. NACA65-210 a=0.2
5. NACA65-210 a=0.0
6. NACA65-211 a=0.5
7. AMES A-03
8. RC-10(N)1
9. NACA64-211 a=0.2
10. BOEING 737 MIDSPAN
11. NACA66-210 a=0.2
12. NACA64-211 a=0.0
13. NACA66-210 a=0.0
14. NACA65-311 a=0.0
15. TsAGI B 10.0% thick
16. NACA65-211 a=0.6
17. HAWKER TEMPEST 96.77% SEMISPAN
18. NACA65-210 a=0.5
19. NACA64-211 a=0.5
20. NACA64-311 a=0.0
21. TsAGI B 10.5% thick