EPPLER 1214 AIRFOIL (e1214-il)
EPPLER 1214 AIRFOIL - Eppler E1214 general aviation airfoil
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(e1214-il) EPPLER 1214 AIRFOIL Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord. Max camber 2.1% at 30.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 1214 AIRFOIL
31.0 31.0
0.0000000 0.0000000
0.0080278 0.0251681
0.0179904 0.0396264
0.0317831 0.0540141
0.0492457 0.0679210
0.0702182 0.0809674
0.0944705 0.0927931
0.1217625 0.1029183
0.1520941 0.1108229
0.1855753 0.1163269
0.2221161 0.1193704
0.2616965 0.1199033
0.3041865 0.1181156
0.3493061 0.1142475
0.3967254 0.1085190
0.4460444 0.1012101
0.4968132 0.0926409
0.5485219 0.0831616
0.6005805 0.0731622
0.6523489 0.0630028
0.7030975 0.0530436
0.7520961 0.0435848
0.7985649 0.0348864
0.8417038 0.0271386
0.8807729 0.0204315
0.9150521 0.0147653
0.9438815 0.0099801
0.9670408 0.0057760
0.9846003 0.0024028
0.9959900 0.0005107
1.0000000 0.0000000
0.0000000 0.0000000
0.0036604 -.0128736
0.0037009 -.0129414
0.0134191 -.0235232
0.0281473 -.0341559
0.0473156 -.0444294
0.0705540 -.0539636
0.0975827 -.0623785
0.1281816 -.0693941
0.1620109 -.0747002
0.1989506 -.0778068
0.2391407 -.0785740
0.2826213 -.0770718
0.3293822 -.0736702
0.3790934 -.0689691
0.4310648 -.0634284
0.4845762 -.0573479
0.5388877 -.0509876
0.5932593 -.0445473
0.6469408 -.0382169
0.6991722 -.0321463
0.7492436 -.0264552
0.7964348 -.0212536
0.8400459 -.0166014
0.8794470 -.0125385
0.9140278 -.0090646
0.9432385 -.0060799
0.9667892 -.0034241
0.9845796 -.0013372
0.9960099 -.0002493
1.0000000 0.0000000
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Polars for EPPLER 1214 AIRFOIL (e1214-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1214-il | 50,000 | 9 | 3.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 5 | 18.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 9 | 25.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 5 | 36.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 9 | 48.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 5 | 54 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 9 | 78.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 5 | 80.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 9 | 105.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 5 | 103.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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