EPPLER 1213 AIRFOIL (e1213-il)
EPPLER 1213 AIRFOIL - Eppler E1213 general aviation airfoil
| Details | Dat file | Parser | |
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(e1213-il) EPPLER 1213 AIRFOIL Eppler E1213 general aviation airfoil Max thickness 17.4% at 22.1% chord. Max camber 2.1% at 35.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER 1213 AIRFOIL
31.0 30.0
0.0000000 0.0000000
0.0071778 0.0222617
0.0168026 0.0356786
0.0302375 0.0490043
0.0473222 0.0618287
0.0678967 0.0737419
0.0917408 0.0842139
0.1189343 0.0927247
0.1496971 0.0991342
0.1838793 0.1035026
0.2212908 0.1057598
0.2617716 0.1059259
0.3050619 0.1041009
0.3508815 0.1004251
0.3988906 0.0950885
0.4486893 0.0883613
0.4998277 0.0805235
0.5517857 0.0719155
0.6039737 0.0628774
0.6557416 0.0537494
0.7063895 0.0448618
0.7551976 0.0364749
0.8013760 0.0288388
0.8441945 0.0221140
0.8829133 0.0163606
0.9168423 0.0115988
0.9453616 0.0076689
0.9682009 0.0043410
0.9853203 0.0017651
0.9962201 0.0003713
1.0000000 0.0000000
0.0000000 0.0000000
0.0042956 -.0132080
0.0141422 -.0236516
0.0285489 -.0340068
0.0470659 -.0437433
0.0694834 -.0524112
0.0956314 -.0595904
0.1254502 -.0649107
0.1589098 -.0680923
0.1961502 -.0689151
0.2374615 -.0675893
0.2826834 -.0647947
0.3311757 -.0610113
0.3822782 -.0564888
0.4353310 -.0514869
0.4896139 -.0461855
0.5444168 -.0407742
0.5990198 -.0353929
0.6526927 -.0301612
0.7047154 -.0252090
0.7544080 -.0206160
0.8010703 -.0164520
0.8440725 -.0127567
0.8828144 -.0095599
0.9167160 -.0068415
0.9452873 -.0045513
0.9682185 -.0025391
0.9853793 -.0009750
0.9962399 -.0001787
1.0000000 0.0000000
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Polars for EPPLER 1213 AIRFOIL (e1213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1213-il | 50,000 | 9 | 11.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 50,000 | 5 | 22.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 100,000 | 5 | 39.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 9 | 51.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 200,000 | 5 | 55.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 9 | 79.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 500,000 | 5 | 80.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 9 | 102.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1213-il | 1,000,000 | 5 | 101.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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