EPPLER 855 AIRFOIL (e855-il)
EPPLER 855 AIRFOIL - Eppler E855 propeller airfoil
| Details | Dat file | Parser | |
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(e855-il) EPPLER 855 AIRFOIL Eppler E855 propeller airfoil Max thickness 15.7% at 32.2% chord. Max camber 3.7% at 50.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 855 AIRFOIL
34. 33.
0.0001900 0.0023300
0.0011600 0.0057800
0.0040000 0.0115000
0.0076600 0.0166800
0.0181500 0.0274200
0.0328900 0.0385500
0.0517700 0.0497200
0.0746500 0.0606800
0.1012900 0.0712100
0.1313800 0.0811000
0.1646100 0.0901200
0.2006200 0.0980200
0.2390400 0.1046000
0.2794600 0.1095400
0.3216500 0.1124900
0.3655300 0.1133000
0.4109500 0.1119800
0.4577700 0.1086400
0.5057300 0.1036700
0.5543500 0.0973800
0.6031000 0.0900700
0.6514400 0.0820100
0.6987700 0.0734700
0.7445099 0.0646900
0.7880500 0.0559100
0.8287800 0.0473300
0.8661400 0.0391000
0.8995500 0.0313500
0.9285300 0.0241500
0.9525800 0.0174300
0.9717100 0.0109100
0.9864200 0.0050800
0.9963600 0.0012400
1.0000000 0.0000000
0.0001900 0.0023300
0.0001900 -.0013800
0.0007300 -.0026800
0.0021300 -.0046800
0.0048500 -.0074200
0.0105800 -.0115600
0.0166700 -.0148800
0.0328900 -.0212800
0.0540300 -.0271100
0.0798900 -.0322300
0.1102200 -.0366400
0.1445800 -.0403300
0.1825300 -.0431800
0.2235800 -.0450900
0.2672100 -.0458300
0.3130900 -.0450900
0.3610300 -.0427100
0.4109100 -.0386300
0.4627600 -.0331200
0.5162900 -.0268800
0.5707900 -.0204700
0.6254500 -.0143100
0.6794500 -.0087500
0.7319000 -.0040400
0.7818900 -.0003600
0.8285500 0.0021900
0.8710200 0.0036300
0.9084700 0.0040500
0.9402000 0.0036800
0.9656600 0.0028200
0.9844500 0.0016900
0.9960600 0.0005300
1.0000000 0.0000000
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Polars for EPPLER 855 AIRFOIL (e855-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e855-il | 50,000 | 9 | 5.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 50,000 | 5 | 23 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 100,000 | 9 | 47 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 100,000 | 5 | 52.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 200,000 | 9 | 76.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 200,000 | 5 | 77.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 500,000 | 9 | 112 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 500,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 1,000,000 | 9 | 140.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 1,000,000 | 5 | 122.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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