EPPLER 682 AIRFOIL (e682-il)
EPPLER 682 AIRFOIL - Eppler E682 sailplane airfoil
| Details | Dat file | Parser | |
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(e682-il) EPPLER 682 AIRFOIL Eppler E682 sailplane airfoil Max thickness 15.3% at 40.4% chord. Max camber 2.9% at 40.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 682 AIRFOIL
32.0 30.0
0.0001700 0.0017100
0.0044600 0.0103100
0.0132800 0.0200600
0.0264900 0.0303800
0.0439700 0.0409100
0.0655400 0.0513200
0.0910300 0.0613300
0.1202700 0.0707100
0.1529900 0.0793100
0.1888900 0.0869600
0.2276400 0.0935000
0.2688900 0.0988400
0.3122400 0.1028800
0.3572600 0.1055500
0.4035200 0.1067600
0.4505900 0.1064900
0.4979900 0.1047300
0.5452300 0.1014600
0.5917800 0.0966500
0.6370400 0.0900200
0.6811300 0.0809500
0.7249000 0.0699000
0.7682500 0.0582800
0.8102000 0.0470700
0.8497800 0.0367100
0.8860800 0.0275100
0.9182500 0.0195300
0.9457200 0.0126500
0.9682300 0.0069700
0.9853400 0.0028800
0.9962300 0.0006500
1.0000000 0.0000000
0.0001700 0.0017100
0.0016600 -.0050100
0.0096100 -.0107100
0.0233300 -.0162700
0.0424600 -.0214300
0.0667400 -.0261100
0.0959500 -.0302900
0.1297400 -.0340100
0.1676800 -.0372800
0.2092900 -.0400800
0.2540900 -.0423900
0.3015200 -.0442000
0.3510500 -.0454900
0.4020700 -.0462300
0.4540100 -.0464100
0.5062500 -.0460200
0.5581700 -.0450200
0.6091500 -.0434200
0.6585300 -.0411200
0.7056700 -.0380000
0.7499400 -.0335600
0.7916700 -.0269900
0.8320900 -.0189500
0.8710300 -.0113200
0.9071500 -.0053100
0.9390100 -.0013700
0.9652000 0.0004500
0.9844700 0.0006900
0.9961200 0.0002600
1.0000000 0.0000000
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Polars for EPPLER 682 AIRFOIL (e682-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e682-il | 50,000 | 9 | 25.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 50,000 | 5 | 21.5 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 100,000 | 9 | 43.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 100,000 | 5 | 37.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 200,000 | 9 | 75.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 200,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 500,000 | 9 | 91.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 500,000 | 5 | 87.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 1,000,000 | 9 | 115.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 1,000,000 | 5 | 105.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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