EPPLER 393 AIRFOIL (e393-il)
EPPLER 393 AIRFOIL - Eppler E393 airfoil
| Details | Dat file | Parser | |
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(e393-il) EPPLER 393 AIRFOIL Eppler E393 airfoil Max thickness 11.5% at 32.3% chord. Max camber 4% at 46% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 393 AIRFOIL
33. 30.
0.0000000 0.0000000
0.0014500 0.0046300
0.0074000 0.0128800
0.0176700 0.0220100
0.0321400 0.0315000
0.0507700 0.0410200
0.0734100 0.0503400
0.0998800 0.0592300
0.1299300 0.0675300
0.1633100 0.0750500
0.1996700 0.0816500
0.2386600 0.0871600
0.2798900 0.0914600
0.3229200 0.0943400
0.3674600 0.0955800
0.4132800 0.0950600
0.4601200 0.0928400
0.5077100 0.0889800
0.5557300 0.0836800
0.6038900 0.0771900
0.6517299 0.0699300
0.6986200 0.0622200
0.7439700 0.0543000
0.7871800 0.0463700
0.8276700 0.0386300
0.8649099 0.0312200
0.8983700 0.0242900
0.9275700 0.0179100
0.9522100 0.0120700
0.9721900 0.0069700
0.9872200 0.0030700
0.9967200 0.0007400
1.0000000 0.0000000
0.0000000 0.0000000
0.0002600 -.0017500
0.0049000 -.0067600
0.0155300 -.0114300
0.0314500 -.0154400
0.0525000 -.0186900
0.0785200 -.0211600
0.1092600 -.0228600
0.1444000 -.0238400
0.1835700 -.0241200
0.2263100 -.0237500
0.2721400 -.0227400
0.3205100 -.0210700
0.3709700 -.0186100
0.4232000 -.0154000
0.4768100 -.0116000
0.5313700 -.0075000
0.5862800 -.0034900
0.6407500 0.0001400
0.6939700 0.0032000
0.7451700 0.0055800
0.7935900 0.0071900
0.8384700 0.0079900
0.8791100 0.0080100
0.9148600 0.0072900
0.9450901 0.0059000
0.9691200 0.0039800
0.9863500 0.0019800
0.9966100 0.0005200
1.0000000 0.0000000
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Polars for EPPLER 393 AIRFOIL (e393-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e393-il | 50,000 | 9 | 35.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e393-il | 50,000 | 5 | 35.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e393-il | 100,000 | 9 | 60.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e393-il | 100,000 | 5 | 62 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e393-il | 200,000 | 9 | 87.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e393-il | 200,000 | 5 | 86.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e393-il | 500,000 | 9 | 124.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e393-il | 500,000 | 5 | 117.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e393-il | 1,000,000 | 9 | 152.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e393-il | 1,000,000 | 5 | 135.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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