EPPLER 548 AIRFOIL (e548-il)
EPPLER 548 AIRFOIL - Eppler E548 general aviation airfoil
| Details | Dat file | Parser | |
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(e548-il) EPPLER 548 AIRFOIL Eppler E548 general aviation airfoil Max thickness 17.4% at 35.4% chord. Max camber 2.2% at 26.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 548 AIRFOIL
35. 38.
0.0000100 0.0003000
0.0001100 0.0019400
0.0004200 0.0036800
0.0012500 0.0064400
0.0030400 0.0104100
0.0105800 0.0209400
0.0224600 0.0321000
0.0385200 0.0434700
0.0586100 0.0546700
0.0825500 0.0654200
0.1101100 0.0754600
0.1410300 0.0845600
0.1750100 0.0925200
0.2117100 0.0991200
0.2507500 0.1041700
0.2917200 0.1073800
0.3343200 0.1083900
0.3785100 0.1068700
0.4245200 0.1028100
0.4723600 0.0967800
0.5215600 0.0893300
0.5715700 0.0808700
0.6217900 0.0717800
0.6715900 0.0624400
0.7202700 0.0531800
0.7671100 0.0442800
0.8113700 0.0359900
0.8523400 0.0284700
0.8893200 0.0218300
0.9216600 0.0161000
0.9488201 0.0112700
0.9702700 0.0071300
0.9860600 0.0034700
0.9963000 0.0008700
1.0000000 0.0000000
0.0000100 0.0003000
0.0000300 -.0004700
0.0001300 -.0012000
0.0003000 -.0018900
0.0005700 -.0025500
0.0009500 -.0032200
0.0014100 -.0038900
0.0025400 -.0052600
0.0039300 -.0066400
0.0064900 -.0087500
0.0130400 -.0130100
0.0283700 -.0201800
0.0488500 -.0271600
0.0741700 -.0338400
0.1040500 -.0401100
0.1381200 -.0459500
0.1759300 -.0513200
0.2169600 -.0561400
0.2606900 -.0602900
0.3066000 -.0636900
0.3541100 -.0662000
0.4026700 -.0677000
0.4517000 -.0680400
0.5006100 -.0670400
0.5487800 -.0642600
0.5962200 -.0590700
0.6435100 -.0514500
0.6910100 -.0422400
0.7384101 -.0326300
0.7847900 -.0235800
0.8291300 -.0156700
0.8703600 -.0092800
0.9074200 -.0045900
0.9393000 -.0015800
0.9651300 0.0000100
0.9842401 0.0004600
0.9960200 0.0002200
1.0000000 0.0000000
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Polars for EPPLER 548 AIRFOIL (e548-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e548-il | 50,000 | 9 | 13.1 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 50,000 | 5 | 10.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 100,000 | 9 | 34.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 100,000 | 5 | 38.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 200,000 | 9 | 61.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 200,000 | 5 | 63.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 500,000 | 9 | 93.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 500,000 | 5 | 90.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e548-il | 1,000,000 | 9 | 117.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e548-il | 1,000,000 | 5 | 108.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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