EPPLER 555 AIRFOIL (e555-il)
EPPLER 555 AIRFOIL - Eppler E555 general aviation airfoil
| Details | Dat file | Parser | |
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(e555-il) EPPLER 555 AIRFOIL Eppler E555 general aviation airfoil Max thickness 16% at 31.9% chord. Max camber 2.6% at 67.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 555 AIRFOIL
35. 38.
0.0000100 0.0004100
0.0001700 0.0020400
0.0005400 0.0037500
0.0014600 0.0064300
0.0044200 0.0119000
0.0131100 0.0220300
0.0261600 0.0325100
0.0434600 0.0429300
0.0648600 0.0530000
0.0902000 0.0624700
0.1192800 0.0711300
0.1518400 0.0788100
0.1875900 0.0853400
0.2261700 0.0905600
0.2673100 0.0942700
0.3107700 0.0963800
0.3562300 0.0969400
0.4032800 0.0959700
0.4515600 0.0935300
0.5006400 0.0897300
0.5501000 0.0847200
0.5994700 0.0786800
0.6482599 0.0718100
0.6959600 0.0643600
0.7420300 0.0565500
0.7859300 0.0486200
0.8270800 0.0408200
0.8649400 0.0332200
0.8989400 0.0263200
0.9285800 0.0199200
0.9533800 0.0142300
0.9729000 0.0091600
0.9872100 0.0045600
0.9965700 0.0011900
1.0000000 0.0000000
0.0000100 0.0004100
0.0000100 -.0003700
0.0000700 -.0011200
0.0002100 -.0018200
0.0004400 -.0025100
0.0007700 -.0032100
0.0011800 -.0039200
0.0022000 -.0053600
0.0034600 -.0068400
0.0057900 -.0091000
0.0098900 -.0123700
0.0231900 -.0201600
0.0413400 -.0278600
0.0640500 -.0352500
0.0910200 -.0421600
0.1219000 -.0484600
0.1562700 -.0540200
0.1936600 -.0586400
0.2335800 -.0620700
0.2755100 -.0639700
0.3192200 -.0637700
0.3647800 -.0612400
0.4122900 -.0563500
0.4619400 -.0494300
0.5135900 -.0412700
0.5666400 -.0326000
0.6203500 -.0239700
0.6739100 -.0158900
0.7264200 -.0087900
0.7769200 -.0029900
0.8244300 0.0013000
0.8679600 0.0040100
0.9065700 0.0051900
0.9394000 0.0050200
0.9656500 0.0038400
0.9847000 0.0021500
0.9961799 0.0006300
1.0000000 0.0000000
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Polars for EPPLER 555 AIRFOIL (e555-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e555-il | 50,000 | 9 | 27.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 50,000 | 5 | 32.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 100,000 | 9 | 51.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 100,000 | 5 | 51.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 200,000 | 9 | 69.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 200,000 | 5 | 67.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 500,000 | 9 | 93.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 500,000 | 5 | 86.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 1,000,000 | 9 | 110.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 1,000,000 | 5 | 99.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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