EPPLER 521 AIRFOIL (e521-il)
EPPLER 521 AIRFOIL - Eppler E521 tailplane airfoil
| Details | Dat file | Parser | |
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(e521-il) EPPLER 521 AIRFOIL Eppler E521 tailplane airfoil Max thickness 13.8% at 37% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 521 AIRFOIL
35. 36.
0.0000500 0.0006600
0.0001800 0.0013400
0.0003800 0.0020400
0.0009500 0.0034900
0.0017400 0.0050000
0.0033000 0.0073300
0.0116500 0.0154200
0.0247200 0.0236800
0.0423100 0.0317400
0.0643200 0.0393200
0.0905600 0.0462400
0.1208500 0.0523600
0.1549400 0.0575900
0.1925400 0.0618600
0.2332800 0.0651400
0.2767700 0.0674100
0.3225600 0.0686400
0.3701900 0.0688400
0.4191400 0.0680200
0.4689000 0.0661900
0.5189300 0.0633500
0.5686700 0.0594500
0.6176700 0.0543700
0.6656900 0.0480700
0.7125599 0.0406000
0.7584201 0.0324200
0.8028300 0.0245900
0.8447100 0.0177700
0.8830500 0.0121400
0.9169900 0.0077600
0.9457800 0.0045100
0.9688900 0.0022200
0.9859200 0.0008000
0.9964300 0.0001500
1.0000000 0.0000000
0.0000500 0.0006600
0.0000500 -.0006600
0.0001800 -.0013400
0.0003800 -.0020400
0.0009500 -.0034900
0.0017400 -.0050000
0.0033000 -.0073300
0.0116500 -.0154200
0.0247200 -.0236800
0.0423100 -.0317400
0.0643200 -.0393200
0.0905600 -.0462400
0.1208500 -.0523600
0.1549400 -.0575900
0.1925400 -.0618600
0.2332800 -.0651400
0.2767700 -.0674100
0.3225600 -.0686400
0.3701900 -.0688400
0.4191400 -.0680200
0.4689000 -.0661900
0.5189300 -.0633500
0.5686700 -.0594500
0.6176700 -.0543700
0.6656900 -.0480700
0.7125599 -.0406000
0.7584201 -.0324200
0.8028300 -.0245900
0.8447100 -.0177700
0.8830500 -.0121400
0.9169900 -.0077500
0.9457800 -.0045100
0.9688900 -.0022200
0.9859200 -.0008000
0.9964300 -.0001500
1.0000000 0.0000000
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Polars for EPPLER 521 AIRFOIL (e521-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e521-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 50,000 | 5 | 29.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 100,000 | 9 | 43.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 100,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 200,000 | 9 | 44.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 200,000 | 5 | 43.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 500,000 | 9 | 58.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 500,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 9 | 70 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 5 | 66.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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