EPPLER 333 AIRFOIL (e333-il)
EPPLER 333 AIRFOIL - Eppler E333 flying wing airfoil
| Details | Dat file | Parser | |
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(e333-il) EPPLER 333 AIRFOIL Eppler E333 flying wing airfoil Max thickness 11.7% at 31.3% chord. Max camber 3.5% at 26.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 333 AIRFOIL
33. 39.
0.0000400 0.0008100
0.0003400 0.0032500
0.0039300 0.0120400
0.0115600 0.0219600
0.0231400 0.0324000
0.0386400 0.0429200
0.0579300 0.0531800
0.0809000 0.0628800
0.1073400 0.0717300
0.1370500 0.0794700
0.1697900 0.0858200
0.2053500 0.0905100
0.2435900 0.0933100
0.2843800 0.0940700
0.3277100 0.0927900
0.3734200 0.0897400
0.4211200 0.0852000
0.4704000 0.0794300
0.5207700 0.0727200
0.5716900 0.0653500
0.6225600 0.0576100
0.6727500 0.0497900
0.7216001 0.0421500
0.7684100 0.0349000
0.8124800 0.0282200
0.8531401 0.0222300
0.8897400 0.0169900
0.9216900 0.0124800
0.9484400 0.0085800
0.9698500 0.0050500
0.9858900 0.0021500
0.9963600 0.0004700
1.0000000 0.0000000
0.0000400 0.0008100
0.0000400 -.0006100
0.0002300 -.0019000
0.0003900 -.0025000
0.0006000 -.0030500
0.0008700 -.0035400
0.0012400 -.0039800
0.0017200 -.0044000
0.0022700 -.0048200
0.0036100 -.0056100
0.0052200 -.0063700
0.0081200 -.0074700
0.0215000 -.0105800
0.0410400 -.0130700
0.0663200 -.0149800
0.0970800 -.0165300
0.1328600 -.0180300
0.1729800 -.0195900
0.2167800 -.0212000
0.2636100 -.0227900
0.3128800 -.0242300
0.3640300 -.0254300
0.4164900 -.0263500
0.4696600 -.0269500
0.5229600 -.0272100
0.5757900 -.0271000
0.6275400 -.0265900
0.6776300 -.0256700
0.7255100 -.0242900
0.7706200 -.0224000
0.8124400 -.0198400
0.8508500 -.0163100
0.8861300 -.0121000
0.9179900 -.0080400
0.9456500 -.0046600
0.9683900 -.0021600
0.9855200 -.0006400
0.9963000 -.0000700
1.0000000 0.0000000
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Polars for EPPLER 333 AIRFOIL (e333-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e333-il | 50,000 | 9 | 17.4 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 50,000 | 5 | 27.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 100,000 | 9 | 40.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 100,000 | 5 | 48 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 200,000 | 9 | 65.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 200,000 | 5 | 68.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 500,000 | 9 | 99.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 500,000 | 5 | 92.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e333-il | 1,000,000 | 9 | 117.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e333-il | 1,000,000 | 5 | 109.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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