E168 (12.45%) (e168-il)
E168 (12.45%) - Eppler E168 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(e168-il) E168 (12.45%) Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E168 (12.45%) 1.00000 0.00000 0.99649 0.00021 0.98631 0.00108 0.97018 0.00271 0.94855 0.00476 0.92146 0.00706 0.88914 0.00979 0.85210 0.01306 0.81090 0.01691 0.76616 0.02130 0.71854 0.02615 0.66871 0.03135 0.61736 0.03673 0.56516 0.04211 0.51275 0.04728 0.46075 0.05200 0.40972 0.05606 0.36019 0.05924 0.31262 0.06134 0.26739 0.06221 0.22485 0.06177 0.18536 0.05995 0.14915 0.05672 0.11641 0.05211 0.08730 0.04627 0.06198 0.03944 0.04069 0.03187 0.02363 0.02380 0.01095 0.01550 0.00287 0.00733 0.00000 0.00000 0.00287 -0.00733 0.01095 -0.01550 0.02363 -0.02380 0.04069 -0.03187 0.06198 -0.03944 0.08730 -0.04627 0.11641 -0.05211 0.14915 -0.05672 0.18536 -0.05995 0.22485 -0.06177 0.26739 -0.06221 0.31262 -0.06134 0.36019 -0.05924 0.40972 -0.05606 0.46075 -0.05200 0.51275 -0.04728 0.56516 -0.04211 0.61736 -0.03673 0.66871 -0.03135 0.71854 -0.02615 0.76616 -0.02130 0.81090 -0.01691 0.85210 -0.01306 0.88914 -0.00979 0.92146 -0.00706 0.94855 -0.00476 0.97018 -0.00271 0.98631 -0.00108 0.99649 -0.00021 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for E168 (12.45%) (e168-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e168-il | 50,000 | 9 | 22.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 100,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 100,000 | 5 | 40.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 200,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 200,000 | 5 | 52.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 500,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 5 | 77.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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