EPPLER 395 AIRFOIL (e395-il)
EPPLER 395 AIRFOIL - Eppler E395 human e664ered aircraft airfoil
| Details | Dat file | Parser | |
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(e395-il) EPPLER 395 AIRFOIL Eppler E395 human e664ered aircraft airfoil Max thickness 12.3% at 29.5% chord. Max camber 5.2% at 52.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 395 AIRFOIL
37. 36.
0.0000100 0.0001300
0.0000400 0.0008100
0.0002900 0.0022500
0.0007300 0.0037800
0.0017500 0.0062300
0.0032300 0.0089100
0.0108800 0.0183300
0.0228100 0.0285000
0.0389100 0.0389900
0.0590600 0.0494800
0.0830900 0.0597000
0.1108200 0.0694300
0.1420000 0.0784500
0.1763600 0.0866000
0.2135800 0.0937200
0.2533100 0.0996700
0.2951600 0.1043000
0.3387600 0.1074800
0.3837500 0.1090800
0.4297600 0.1090400
0.4764500 0.1073200
0.5234600 0.1039500
0.5704500 0.0989700
0.6171000 0.0924800
0.6631700 0.0847000
0.7083100 0.0760100
0.7520000 0.0667800
0.7937300 0.0573300
0.8329500 0.0479700
0.8691100 0.0389400
0.9016800 0.0304800
0.9301300 0.0227700
0.9539500 0.0158400
0.9729800 0.0096000
0.9873400 0.0044000
0.9966900 0.0010800
1.0000000 0.0000000
0.0000100 0.0001300
0.0000200 -.0005200
0.0001100 -.0011200
0.0003000 -.0017100
0.0005800 -.0023000
0.0009300 -.0029000
0.0018300 -.0041100
0.0029500 -.0053400
0.0050400 -.0072000
0.0115400 -.0113800
0.0250500 -.0168500
0.0433600 -.0213400
0.0664100 -.0246800
0.0940800 -.0267400
0.1262600 -.0275000
0.1627400 -.0269600
0.2033000 -.0252000
0.2476600 -.0223400
0.2954800 -.0185900
0.3463100 -.0142100
0.3996000 -.0094900
0.4547200 -.0046600
0.5109900 0.0000300
0.5677000 0.0043600
0.6240900 0.0081200
0.6793600 0.0111200
0.7327200 0.0132400
0.7833400 0.0143700
0.8304100 0.0144600
0.8731400 0.0135600
0.9107600 0.0117400
0.9425800 0.0091400
0.9678299 0.0060100
0.9858400 0.0029600
0.9964900 0.0007800
1.0000000 0.0000000
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Polars for EPPLER 395 AIRFOIL (e395-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e395-il | 50,000 | 9 | 31 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 50,000 | 5 | 28.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 100,000 | 9 | 59.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 100,000 | 5 | 61.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 200,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 200,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 500,000 | 9 | 136.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 500,000 | 5 | 128.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 9 | 169.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 5 | 144.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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