EPPLER 1200 AIRFOIL (e1200-il)
EPPLER 1200 AIRFOIL - Eppler E1200 general aviation airfoil
| Details | Dat file | Parser | |
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(e1200-il) EPPLER 1200 AIRFOIL Eppler E1200 general aviation airfoil Max thickness 16.9% at 36.1% chord. Max camber 3.5% at 50.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 1200 AIRFOIL
33.0 30.0
0.0000000 0.0000000
0.0013220 0.0072612
0.0065853 0.0188100
0.0159290 0.0310076
0.0293227 0.0433341
0.0467364 0.0553794
0.0681101 0.0668236
0.0933636 0.0774067
0.1223668 0.0869288
0.1549898 0.0952398
0.1910125 0.1023098
0.2301150 0.1081789
0.2718071 0.1128172
0.3156289 0.1161650
0.3610904 0.1181422
0.4076715 0.1186891
0.4548522 0.1177158
0.5021124 0.1150724
0.5490720 0.1105291
0.5955412 0.1039759
0.6414397 0.0954028
0.6868677 0.0851498
0.7316154 0.0739870
0.7750631 0.0625846
0.8165308 0.0514027
0.8553086 0.0408615
0.8906666 0.0312414
0.9219148 0.0227524
0.9483633 0.0154048
0.9696720 0.0090787
0.9858308 0.0040441
0.9963002 0.0009611
1.0000000 -.0000000
0.0000000 0.0000000
0.0049522 -.0106754
0.0049970 -.0107202
0.0161252 -.0177734
0.0327137 -.0243882
0.0544324 -.0303845
0.0810215 -.0356521
0.1122009 -.0401309
0.1476605 -.0438410
0.1869905 -.0468221
0.2296807 -.0490842
0.2751912 -.0505970
0.3229620 -.0513305
0.3724030 -.0512144
0.4229043 -.0501786
0.4738359 -.0480129
0.5248280 -.0443971
0.5757204 -.0392414
0.6264533 -.0325955
0.6771064 -.0249296
0.7273197 -.0172036
0.7762026 -.0101872
0.8227552 -.0043602
0.8659472 -.0000723
0.9047088 0.0025569
0.9380398 0.0035375
0.9649002 0.0030899
0.9844002 0.0018044
0.9961101 0.0005311
1.0000000 -.0000000
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Polars for EPPLER 1200 AIRFOIL (e1200-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1200-il | 50,000 | 9 | 9.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 50,000 | 5 | 23.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 100,000 | 9 | 46.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 100,000 | 5 | 39.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 200,000 | 9 | 69.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 200,000 | 5 | 68.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 500,000 | 5 | 96.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 1,000,000 | 9 | 131.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 1,000,000 | 5 | 109.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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