EPPLER 502 AIRFOIL (e502-il)
EPPLER 502 AIRFOIL - Eppler E502 general purpose airfoil
| Details | Dat file | Parser | |
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(e502-il) EPPLER 502 AIRFOIL Eppler E502 general purpose airfoil Max thickness 15.6% at 42.1% chord. Max camber 1.5% at 32.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 502 AIRFOIL
36. 37.
0.0000100 0.0001100
0.0000600 0.0007400
0.0001800 0.0014000
0.0006000 0.0027900
0.0012400 0.0042700
0.0025800 0.0066100
0.0075100 0.0126000
0.0184300 0.0215900
0.0339000 0.0308800
0.0537500 0.0401800
0.0778000 0.0492100
0.1058400 0.0577800
0.1375800 0.0657300
0.1727200 0.0729000
0.2109100 0.0791500
0.2517600 0.0843800
0.2948400 0.0884700
0.3396900 0.0913400
0.3858400 0.0928700
0.4327800 0.0929600
0.4799700 0.0913900
0.5271200 0.0878700
0.5741400 0.0822700
0.6210100 0.0746100
0.6679300 0.0653500
0.7146299 0.0554100
0.7603500 0.0455200
0.8042600 0.0361800
0.8455100 0.0277600
0.8832300 0.0204500
0.9166300 0.0143600
0.9449500 0.0093800
0.9677900 0.0052600
0.9850500 0.0021400
0.9961300 0.0004500
1.0000000 0.0000000
0.0000100 0.0001100
0.0000300 -.0004800
0.0001600 -.0010700
0.0003800 -.0016600
0.0006700 -.0022800
0.0014600 -.0035300
0.0024800 -.0048200
0.0044400 -.0068000
0.0067400 -.0087100
0.0182600 -.0152500
0.0351500 -.0216000
0.0571800 -.0277800
0.0839900 -.0337300
0.1152200 -.0393600
0.1505000 -.0445700
0.1894100 -.0493000
0.2315000 -.0534600
0.2762900 -.0570100
0.3232900 -.0598900
0.3718900 -.0621100
0.4214700 -.0635600
0.4714100 -.0640900
0.5211800 -.0635300
0.5702100 -.0617500
0.6179300 -.0583800
0.6643800 -.0528000
0.7102900 -.0453000
0.7555900 -.0370700
0.7994800 -.0289800
0.8410800 -.0215800
0.8794600 -.0151900
0.9137500 -.0100100
0.9430900 -.0060200
0.9669001 -.0030200
0.9847900 -.0010400
0.9961000 -.0001600
1.0000000 0.0000000
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Polars for EPPLER 502 AIRFOIL (e502-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e502-il | 50,000 | 9 | 24.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 50,000 | 5 | 21 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 100,000 | 9 | 45.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 100,000 | 5 | 36.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 200,000 | 9 | 58.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 200,000 | 5 | 58 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 500,000 | 9 | 88 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 500,000 | 5 | 80 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 1,000,000 | 9 | 106.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 1,000,000 | 5 | 90.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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