EPPLER 553 AIRFOIL (e553-il)
EPPLER 553 AIRFOIL - Eppler E553 general aviation airfoil
| Details | Dat file | Parser | |
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(e553-il) EPPLER 553 AIRFOIL Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord. Max camber 2.9% at 56.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 553 AIRFOIL
35. 38.
0.0000200 0.0005100
0.0001800 0.0022800
0.0005400 0.0041300
0.0014600 0.0070600
0.0052800 0.0143900
0.0145500 0.0256500
0.0281300 0.0373900
0.0458500 0.0491900
0.0675600 0.0607300
0.0930400 0.0717200
0.1220700 0.0819400
0.1543700 0.0911400
0.1896200 0.0991200
0.2274800 0.1056300
0.2676300 0.1104900
0.3098400 0.1134300
0.3538600 0.1143800
0.3994900 0.1133200
0.4464500 0.1104000
0.4943700 0.1057700
0.5428600 0.0996200
0.5914900 0.0921800
0.6398200 0.0837100
0.6873500 0.0745000
0.7335700 0.0648700
0.7779200 0.0551400
0.8198200 0.0456300
0.8586700 0.0366100
0.8938301 0.0283300
0.9247100 0.0209500
0.9507300 0.0145900
0.9713400 0.0091500
0.9865100 0.0044500
0.9964000 0.0011400
1.0000000 0.0000000
0.0000200 0.0005100
0.0000200 -.0003300
0.0000900 -.0011400
0.0002400 -.0019000
0.0004900 -.0026400
0.0008400 -.0034000
0.0012600 -.0041600
0.0023200 -.0057200
0.0036300 -.0073000
0.0060300 -.0097300
0.0089000 -.0121800
0.0219200 -.0204700
0.0398800 -.0286800
0.0624500 -.0365700
0.0893400 -.0439600
0.1201800 -.0507200
0.1545400 -.0566900
0.1919400 -.0616900
0.2318900 -.0654600
0.2738700 -.0676300
0.3176500 -.0676700
0.3633000 -.0653200
0.4109000 -.0605600
0.4606400 -.0537100
0.5123800 -.0455600
0.5655000 -.0368300
0.6192800 -.0280800
0.6729100 -.0198300
0.7254699 -.0124800
0.7760200 -.0063600
0.8235700 -.0016900
0.8671400 0.0014500
0.9058000 0.0031100
0.9386700 0.0034800
0.9650400 0.0028900
0.9843200 0.0017300
0.9960600 0.0005300
1.0000000 0.0000000
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Polars for EPPLER 553 AIRFOIL (e553-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e553-il | 50,000 | 9 | 4.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 50,000 | 5 | 17.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 100,000 | 9 | 45.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 100,000 | 5 | 49.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 200,000 | 9 | 71.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 200,000 | 5 | 69.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 500,000 | 9 | 99.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 500,000 | 5 | 93.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 1,000,000 | 9 | 121.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 1,000,000 | 5 | 111.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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