EPPLER 554 AIRFOIL (e554-il)
EPPLER 554 AIRFOIL - Eppler E554 general aviation airfoil
| Details | Dat file | Parser | |
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(e554-il) EPPLER 554 AIRFOIL Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord. Max camber 2.7% at 56.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 554 AIRFOIL
35. 38.
0.0000100 0.0003400
0.0001100 0.0021400
0.0004300 0.0040400
0.0012600 0.0070300
0.0051500 0.0150400
0.0142200 0.0266100
0.0275100 0.0386700
0.0448600 0.0507800
0.0661100 0.0626200
0.0910500 0.0738800
0.1194400 0.0843100
0.1510200 0.0936500
0.1854600 0.1016800
0.2224300 0.1081400
0.2616000 0.1127300
0.3027200 0.1151800
0.3456500 0.1151800
0.3905600 0.1126700
0.4374100 0.1081000
0.4857700 0.1019100
0.5351500 0.0944400
0.5850200 0.0860200
0.6347900 0.0769900
0.6838500 0.0676700
0.7315200 0.0583400
0.7771400 0.0492800
0.8200400 0.0407000
0.8595300 0.0327500
0.8950200 0.0255600
0.9259101 0.0191800
0.9517100 0.0136100
0.9719800 0.0087300
0.9868200 0.0043300
0.9964800 0.0011200
1.0000000 0.0000000
0.0000100 0.0003400
0.0000300 -.0005200
0.0001300 -.0013400
0.0003000 -.0021200
0.0005700 -.0028800
0.0009400 -.0036400
0.0013800 -.0044200
0.0024800 -.0060000
0.0038400 -.0076000
0.0063000 -.0100400
0.0087700 -.0121400
0.0217900 -.0204400
0.0397600 -.0286400
0.0623600 -.0365000
0.0892700 -.0438400
0.1201400 -.0505400
0.1545200 -.0564500
0.1919500 -.0613700
0.2319300 -.0650700
0.2739300 -.0671700
0.3177300 -.0671700
0.3634000 -.0647100
0.4110100 -.0598800
0.4607600 -.0529700
0.5125200 -.0447600
0.5656600 -.0359800
0.6194600 -.0272000
0.6731000 -.0189200
0.7256900 -.0115700
0.7762600 -.0054700
0.8238400 -.0008400
0.8674300 0.0022200
0.9061100 0.0037800
0.9390000 0.0040000
0.9653500 0.0032100
0.9845200 0.0018600
0.9961200 0.0005600
1.0000000 0.0000000
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Polars for EPPLER 554 AIRFOIL (e554-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e554-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 50,000 | 5 | 18.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 100,000 | 9 | 36.4 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 100,000 | 5 | 46.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 200,000 | 9 | 69 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 200,000 | 5 | 70.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 500,000 | 9 | 103.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 500,000 | 5 | 98.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 9 | 127.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 5 | 118.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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