EPPLER 520 AIRFOIL (e520-il)
EPPLER 520 AIRFOIL - Eppler E520 tailplane airfoil
| Details | Dat file | Parser | |
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(e520-il) EPPLER 520 AIRFOIL Eppler E520 tailplane airfoil Max thickness 15% at 36.7% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 520 AIRFOIL
35. 36.
0.0000500 0.0007000
0.0001800 0.0014300
0.0003800 0.0021800
0.0009500 0.0037300
0.0017400 0.0053300
0.0033100 0.0078100
0.0117100 0.0164000
0.0248100 0.0251900
0.0424200 0.0338000
0.0644100 0.0419700
0.0905900 0.0494900
0.1207500 0.0562200
0.1546300 0.0620400
0.1919100 0.0668600
0.2324400 0.0706200
0.2752300 0.0732600
0.3204400 0.0747500
0.3674000 0.0750400
0.4156400 0.0741100
0.4646900 0.0719400
0.5140000 0.0685100
0.5631300 0.0636400
0.6118600 0.0572800
0.6600800 0.0494400
0.7079700 0.0405900
0.7552000 0.0318500
0.8006400 0.0239900
0.8432500 0.0172600
0.8821000 0.0117800
0.9164000 0.0075300
0.9454500 0.0043800
0.9687100 0.0021700
0.9858400 0.0007800
0.9964100 0.0001400
1.0000000 0.0000000
0.0000500 0.0007000
0.0000500 -.0007000
0.0001800 -.0014300
0.0003800 -.0021800
0.0009500 -.0037300
0.0017400 -.0053300
0.0033100 -.0078100
0.0117100 -.0164000
0.0248100 -.0251900
0.0424200 -.0338000
0.0644100 -.0419700
0.0905900 -.0494900
0.1207500 -.0562200
0.1546300 -.0620400
0.1919100 -.0668600
0.2322400 -.0706200
0.2752300 -.0732600
0.3204400 -.0747500
0.3674000 -.0750400
0.4156400 -.0741100
0.4646900 -.0719400
0.5140000 -.0685100
0.5631300 -.0636400
0.6118600 -.0572800
0.6600800 -.0494400
0.7079700 -.0405900
0.7552000 -.0318500
0.8006400 -.0239900
0.8432500 -.0172600
0.8821000 -.0117800
0.9164000 -.0075200
0.9454500 -.0043800
0.9687100 -.0021700
0.9858400 -.0007800
0.9964100 -.0001400
1.0000000 0.0000000
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Polars for EPPLER 520 AIRFOIL (e520-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e520-il | 50,000 | 9 | 28.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 50,000 | 5 | 27.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 100,000 | 9 | 41.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 100,000 | 5 | 35.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 200,000 | 9 | 47.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 200,000 | 5 | 45.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 500,000 | 9 | 62.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 500,000 | 5 | 57.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e520-il | 1,000,000 | 9 | 71.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e520-il | 1,000,000 | 5 | 67.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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