EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 50,000 Max Cl/Cd: 11.52 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1213-il-50000.txt Download as CSV file: xf-e1213-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1213 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3946 0.13353 0.12575 0.0074 1.0000 0.3349
-11.250 -0.3569 0.12735 0.11950 0.0075 1.0000 0.3457
-11.000 -0.3821 0.12771 0.11994 0.0067 1.0000 0.3543
-10.750 -0.3412 0.12142 0.11358 0.0067 1.0000 0.3649
-10.500 -0.3628 0.12125 0.11348 0.0061 1.0000 0.3743
-10.250 -0.3252 0.11574 0.10792 0.0060 1.0000 0.3854
-10.000 -0.3386 0.11457 0.10681 0.0057 1.0000 0.3950
-9.750 -0.3098 0.11038 0.10259 0.0056 1.0000 0.4073
-9.500 -0.3115 0.10811 0.10036 0.0054 1.0000 0.4166
-9.250 -0.3007 0.10585 0.09812 0.0055 1.0000 0.4307
-9.000 -0.2840 0.10214 0.09442 0.0051 1.0000 0.4396
-8.750 -0.3079 0.10279 0.09518 0.0062 1.0000 0.4538
-8.500 -0.2603 0.09689 0.08922 0.0051 1.0000 0.4646
-8.250 -0.2615 0.09502 0.08742 0.0054 1.0000 0.4773
-8.000 -0.2670 0.09447 0.08694 0.0065 1.0000 0.4935
-7.750 -0.2284 0.08948 0.08196 0.0052 1.0000 0.5035
-7.500 -0.2265 0.08768 0.08023 0.0058 1.0000 0.5183
-7.250 -0.2382 0.08759 0.08027 0.0076 1.0000 0.5352
-7.000 -0.1929 0.08269 0.07538 0.0056 1.0000 0.5474
-6.750 -0.1819 0.08050 0.07330 0.0058 1.0000 0.5625
-6.500 -0.1788 0.07903 0.07197 0.0066 1.0000 0.5791
-6.250 -0.1894 0.07903 0.07218 0.0090 1.0000 0.5965
-6.000 -0.4514 0.07198 0.06551 0.0067 0.9894 0.4137
-5.750 -0.4018 0.06678 0.06015 -0.0034 0.9696 0.4105
-5.500 -0.3724 0.06106 0.05425 -0.0136 0.9494 0.4090
-5.250 -0.3530 0.05572 0.04869 -0.0220 0.9290 0.4092
-5.000 -0.3397 0.05043 0.04305 -0.0297 0.9101 0.4124
-4.750 -0.2794 0.04903 0.04166 -0.0340 0.8937 0.4207
-4.500 -0.2544 0.04644 0.03885 -0.0373 0.8757 0.4270
-4.250 -0.2433 0.04357 0.03563 -0.0397 0.8583 0.4326
-4.000 -0.2066 0.04249 0.03452 -0.0407 0.8417 0.4392
-3.750 -0.1856 0.04141 0.03331 -0.0406 0.8246 0.4460
-3.500 -0.1751 0.03995 0.03155 -0.0405 0.8079 0.4526
-3.250 -0.1523 0.03933 0.03092 -0.0397 0.7917 0.4584
-3.000 -0.1309 0.03875 0.03025 -0.0390 0.7767 0.4656
-2.750 -0.1086 0.03763 0.02880 -0.0391 0.7644 0.4743
-2.500 -0.0889 0.03745 0.02869 -0.0376 0.7485 0.4806
-2.250 -0.0713 0.03717 0.02831 -0.0367 0.7342 0.4884
-2.000 -0.0478 0.03661 0.02758 -0.0361 0.7224 0.4972
-1.750 -0.0269 0.03649 0.02746 -0.0350 0.7086 0.5059
-1.500 -0.0102 0.03640 0.02722 -0.0344 0.6954 0.5151
-1.250 0.0196 0.03599 0.02680 -0.0333 0.6855 0.5252
-1.000 0.0333 0.03629 0.02701 -0.0326 0.6712 0.5357
-0.750 0.0558 0.03637 0.02715 -0.0314 0.6600 0.5467
-0.500 0.0783 0.03636 0.02709 -0.0307 0.6486 0.5592
-0.250 0.0953 0.03685 0.02759 -0.0299 0.6367 0.5722
0.000 0.1233 0.03665 0.02740 -0.0289 0.6270 0.5887
0.250 0.1350 0.03759 0.02841 -0.0279 0.6148 0.6033
0.500 0.1654 0.03726 0.02808 -0.0268 0.6064 0.6252
0.750 0.1724 0.03859 0.02953 -0.0258 0.5940 0.6438
1.000 0.2036 0.03820 0.02917 -0.0245 0.5864 0.6763
1.250 0.2041 0.04000 0.03120 -0.0231 0.5745 0.7010
1.500 0.2351 0.03946 0.03087 -0.0209 0.5670 0.7505
1.750 0.2310 0.04163 0.03337 -0.0193 0.5560 0.7985
2.000 0.3435 0.04155 0.03357 -0.0292 0.5422 0.9280
2.250 0.4725 0.04100 0.03267 -0.0460 0.5270 1.0000
2.500 0.4213 0.04498 0.03661 -0.0421 0.5195 1.0000
2.750 0.4200 0.04677 0.03823 -0.0401 0.5119 1.0000
3.000 0.4467 0.04707 0.03831 -0.0387 0.5054 1.0000
3.250 0.3867 0.05331 0.04456 -0.0365 0.4986 1.0000
3.500 0.3818 0.05596 0.04710 -0.0352 0.4930 1.0000
3.750 0.4164 0.05643 0.04743 -0.0345 0.4857 1.0000
4.000 0.3688 0.06161 0.05255 -0.0326 0.4836 1.0000
4.250 0.3531 0.06534 0.05620 -0.0321 0.4831 1.0000
4.500 0.3468 0.06875 0.05955 -0.0321 0.4837 1.0000
4.750 0.3459 0.07200 0.06273 -0.0323 0.4846 1.0000
5.000 0.3568 0.07522 0.06591 -0.0330 0.4884 1.0000
5.250 0.2417 0.08428 0.07515 -0.0379 0.5989 1.0000
5.500 0.2661 0.08688 0.07767 -0.0385 0.5881 1.0000
5.750 0.2670 0.08866 0.07938 -0.0376 0.5791 1.0000
6.000 0.2908 0.09126 0.08191 -0.0380 0.5685 1.0000
6.250 0.2976 0.09371 0.08430 -0.0379 0.5623 1.0000
6.500 0.3058 0.09535 0.08589 -0.0374 0.5511 1.0000
6.750 0.3496 0.10062 0.09111 -0.0394 0.5459 1.0000
7.000 0.3253 0.09981 0.09025 -0.0371 0.5336 1.0000
7.250 0.3634 0.10427 0.09467 -0.0384 0.5270 1.0000
7.500 0.3458 0.10454 0.09489 -0.0370 0.5174 1.0000
7.750 0.3680 0.10754 0.09787 -0.0375 0.5101 1.0000
8.000 0.3906 0.11168 0.10197 -0.0383 0.5059 1.0000
8.250 0.3799 0.11180 0.10207 -0.0373 0.4943 1.0000
8.500 0.4159 0.11649 0.10673 -0.0384 0.4884 1.0000
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Polar data table (+)
Polar graphs
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