EPPLER 654 AIRFOIL (e654-il)
EPPLER 654 AIRFOIL - Eppler E654 sailplane airfoil
| Details | Dat file | Parser | |
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(e654-il) EPPLER 654 AIRFOIL Eppler E654 sailplane airfoil Max thickness 17.2% at 36.1% chord. Max camber 4.9% at 46.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 654 AIRFOIL
35. 38.
0.0000100 -.0005700
0.0000400 0.0012600
0.0004300 0.0041900
0.0028100 0.0115300
0.0098500 0.0232100
0.0210600 0.0356100
0.0363600 0.0483100
0.0556300 0.0609400
0.0787400 0.0732100
0.1055000 0.0848600
0.1356900 0.0956500
0.1690600 0.1054100
0.2052900 0.1139500
0.2440600 0.1211200
0.2850000 0.1267900
0.3276900 0.1308500
0.3717300 0.1331900
0.4166300 0.1337000
0.4619400 0.1322100
0.5073300 0.1284600
0.5526400 0.1223200
0.5978500 0.1137100
0.6432100 0.1029600
0.6886100 0.0909400
0.7334200 0.0784200
0.7769400 0.0659400
0.8184300 0.0539300
0.8571500 0.0427600
0.8923500 0.0326600
0.9233400 0.0238100
0.9494500 0.0161800
0.9703900 0.0095900
0.9861900 0.0043100
0.9964000 0.0010400
1.0000000 0.0000000
0.0000100 -.0005700
0.0001600 -.0022800
0.0003100 -.0030900
0.0005200 -.0038500
0.0008000 -.0045500
0.0011700 -.0052200
0.0016500 -.0058900
0.0022100 -.0065500
0.0035300 -.0078800
0.0051300 -.0091900
0.0079700 -.0111500
0.0114600 -.0131500
0.0263100 -.0192000
0.0464900 -.0245700
0.0717400 -.0291700
0.1117700 -.0339700
0.1362700 -.0359500
0.1748500 -.0381200
0.2170900 -.0395100
0.2624900 -.0401500
0.3105200 -.0400600
0.3606200 -.0392500
0.4121900 -.0377300
0.4646000 -.0354800
0.5172600 -.0324200
0.5696100 -.0283900
0.6213800 -.0231600
0.6726000 -.0169300
0.7230800 -.0102800
0.7723500 -.0039300
0.8195900 0.0013100
0.8636400 0.0049200
0.9033300 0.0067100
0.9375200 0.0066600
0.9649700 0.0050200
0.9846200 0.0026600
0.9962000 0.0007300
1.0000000 0.0000000
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Polars for EPPLER 654 AIRFOIL (e654-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e654-il | 50,000 | 9 | 5.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 50,000 | 5 | 12.8 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 100,000 | 9 | 32.7 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 100,000 | 5 | 28.3 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 200,000 | 9 | 70.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 200,000 | 5 | 71.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 500,000 | 9 | 122.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 500,000 | 5 | 118 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e654-il | 1,000,000 | 9 | 158.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e654-il | 1,000,000 | 5 | 145.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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