EPPLER 587 AIRFOIL (e587-il)
EPPLER 587 AIRFOIL - Eppler E587 sailplane airfoil
| Details | Dat file | Parser | |
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(e587-il) EPPLER 587 AIRFOIL Eppler E587 sailplane airfoil Max thickness 16.6% at 41.1% chord. Max camber 4.2% at 51.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 587 AIRFOIL
36. 37.
0.0000100 -.0002700
0.0000300 0.0012900
0.0002500 0.0029700
0.0009400 0.0056700
0.0030700 0.0107000
0.0105100 0.0214400
0.0221900 0.0329800
0.0380000 0.0448600
0.0578100 0.0567100
0.0815000 0.0682200
0.1088700 0.0791300
0.1397100 0.0892300
0.1737600 0.0983300
0.2107200 0.1062500
0.2502400 0.1128800
0.2919800 0.1180700
0.3355200 0.1217400
0.3804600 0.1237900
0.4263600 0.1241300
0.4728400 0.1226600
0.5195200 0.1193400
0.5661100 0.1141400
0.6123300 0.1071500
0.6579600 0.0985100
0.7028300 0.0885700
0.7465600 0.0778900
0.7885600 0.0669500
0.8282100 0.0560900
0.8649200 0.0455900
0.8981100 0.0357000
0.9272500 0.0266300
0.9518200 0.0184700
0.9715700 0.0111800
0.9866000 0.0051500
0.9964700 0.0012800
1.0000000 0.0000000
0.0000100 -.0002700
0.0000700 -.0010000
0.0001900 -.0016900
0.0004000 -.0023300
0.0007000 -.0029300
0.0011100 -.0035400
0.0015900 -.0041400
0.0027900 -.0053500
0.0042600 -.0065600
0.0069200 -.0083900
0.0123000 -.0113200
0.0275200 -.0170800
0.0480800 -.0223300
0.0737000 -.0270100
0.1041000 -.0311100
0.1388700 -.0346500
0.1775700 -.0376200
0.2196800 -.0400000
0.2646800 -.0417200
0.3119900 -.0427500
0.3610000 -.0429900
0.4111000 -.0423300
0.4616400 -.0404800
0.5123100 -.0370000
0.5631100 -.0317700
0.6140700 -.0249100
0.6653600 -.0169700
0.7166400 -.0090500
0.7669700 -.0020400
0.8152600 0.0034900
0.8603300 0.0071200
0.9009900 0.0087300
0.9360600 0.0083000
0.9642100 0.0061400
0.9843300 0.0032300
0.9961400 0.0008800
1.0000000 0.0000000
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Polars for EPPLER 587 AIRFOIL (e587-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e587-il | 50,000 | 9 | 7.3 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 50,000 | 5 | 18.2 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 100,000 | 9 | 44.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 100,000 | 5 | 41.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 200,000 | 9 | 75.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 200,000 | 5 | 75.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 500,000 | 9 | 116.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 500,000 | 5 | 110 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 1,000,000 | 9 | 145.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 1,000,000 | 5 | 131.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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