EPPLER 550 AIRFOIL (e550-il)
EPPLER 550 AIRFOIL - Eppler E550 general aviation airfoil
| Details | Dat file | Parser | |
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(e550-il) EPPLER 550 AIRFOIL Eppler E550 general aviation airfoil Max thickness 18.2% at 34% chord. Max camber 2.2% at 29.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 550 AIRFOIL
35. 38.
0.0000100 0.0003600
0.0001300 0.0020800
0.0004500 0.0038900
0.0013000 0.0067700
0.0038600 0.0122500
0.0120500 0.0232700
0.0245500 0.0348600
0.0412000 0.0465900
0.0618400 0.0581300
0.0862700 0.0691700
0.1142800 0.0794600
0.1455900 0.0887800
0.1798900 0.0969100
0.2168500 0.1036400
0.2560800 0.1087700
0.2971700 0.1120300
0.3398200 0.1130500
0.3839800 0.1114800
0.4299100 0.1073400
0.4775900 0.1011900
0.5265700 0.0935800
0.5763000 0.0849300
0.6261900 0.0756100
0.6756099 0.0660000
0.7238600 0.0564300
0.7702301 0.0472000
0.8140200 0.0385400
0.8545099 0.0306400
0.8910200 0.0236000
0.9229300 0.0174800
0.9496800 0.0122600
0.9707900 0.0077700
0.9862900 0.0038000
0.9963500 0.0009600
1.0000000 0.0000000
0.0000100 0.0003600
0.0000300 -.0004500
0.0001200 -.0012200
0.0002900 -.0019500
0.0005600 -.0026500
0.0009300 -.0033600
0.0013800 -.0040800
0.0024900 -.0055400
0.0038700 -.0070200
0.0063900 -.0092900
0.0112800 -.0128600
0.0257200 -.0205800
0.0452300 -.0281500
0.0695100 -.0354100
0.0982600 -.0422400
0.1311000 -.0485800
0.1676000 -.0543300
0.2072600 -.0594000
0.2495700 -.0636200
0.2940000 -.0668600
0.3400000 -.0689300
0.3870100 -.0696100
0.4344300 -.0684700
0.4821800 -.0648700
0.5307300 -.0586500
0.5804400 -.0504400
0.6311200 -.0412700
0.6820000 -.0320300
0.7322100 -.0232900
0.7808100 -.0155800
0.8268000 -.0092000
0.8691700 -.0043800
0.9069500 -.0011400
0.9392200 0.0006400
0.9652200 0.0012400
0.9843400 0.0009900
0.9960501 0.0003500
1.0000000 0.0000000
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Polars for EPPLER 550 AIRFOIL (e550-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e550-il | 50,000 | 9 | 12.6 at α=-2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 50,000 | 5 | 11.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 100,000 | 9 | 33.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 100,000 | 5 | 40.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 200,000 | 9 | 66 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 200,000 | 5 | 67 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 500,000 | 9 | 99.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 500,000 | 5 | 95.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e550-il | 1,000,000 | 9 | 124.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e550-il | 1,000,000 | 5 | 114.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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