EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 200,000 Max Cl/Cd: 79.78 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e431-il-200000.txt Download as CSV file: xf-e431-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 431 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1371 0.09263 0.08919 -0.0991 0.9575 0.0442
-9.500 -0.1300 0.08769 0.08426 -0.1049 0.9508 0.0460
-9.250 -0.1389 0.07588 0.07239 -0.1268 0.9451 0.0473
-9.000 -0.1205 0.07315 0.06974 -0.1240 0.9403 0.0483
-8.750 -0.0990 0.07113 0.06770 -0.1242 0.9362 0.0496
-8.500 -0.0854 0.06558 0.06212 -0.1320 0.9315 0.0514
-8.250 -0.0906 0.06055 0.05700 -0.1375 0.9203 0.0524
-8.000 -0.1026 0.05674 0.05303 -0.1399 0.9094 0.0539
-7.750 -0.1389 0.05521 0.05079 -0.1389 0.8952 0.0564
-7.500 -0.1261 0.04978 0.04553 -0.1394 0.8897 0.0577
-7.250 -0.1074 0.04720 0.04294 -0.1400 0.8854 0.0592
-7.000 -0.1001 0.04524 0.04087 -0.1387 0.8788 0.0615
-6.750 -0.1061 0.04340 0.03841 -0.1363 0.8707 0.0679
-6.500 -0.0832 0.04004 0.03511 -0.1372 0.8676 0.0698
-6.250 -0.0903 0.03002 0.02375 -0.1303 0.8590 0.0290
-6.000 -0.0689 0.02725 0.02053 -0.1292 0.8550 0.0260
-5.750 -0.0427 0.02447 0.01718 -0.1287 0.8520 0.0242
-5.500 -0.0251 0.02316 0.01557 -0.1267 0.8463 0.0240
-5.250 -0.0016 0.02202 0.01434 -0.1259 0.8416 0.0247
-5.000 0.0261 0.02091 0.01309 -0.1258 0.8383 0.0259
-4.750 0.0552 0.02000 0.01209 -0.1261 0.8356 0.0294
-4.500 0.0717 0.01967 0.01175 -0.1242 0.8298 0.0320
-4.250 0.0935 0.01883 0.01093 -0.1232 0.8252 0.0354
-4.000 0.1190 0.01800 0.01009 -0.1229 0.8219 0.0414
-3.750 0.1463 0.01716 0.00933 -0.1230 0.8192 0.0619
-3.500 0.1587 0.01650 0.00902 -0.1208 0.8128 0.1205
-3.250 0.1765 0.01490 0.00860 -0.1206 0.8084 0.3767
-3.000 0.1935 0.01441 0.00925 -0.1177 0.8052 0.6889
-2.750 0.2206 0.01491 0.00965 -0.1164 0.8027 0.7386
-2.500 0.2335 0.01554 0.01024 -0.1131 0.7962 0.7625
-2.250 0.2530 0.01600 0.01065 -0.1104 0.7921 0.7811
-2.000 0.2762 0.01634 0.01090 -0.1083 0.7891 0.7979
-1.750 0.3011 0.01662 0.01107 -0.1066 0.7867 0.8132
-1.500 0.3083 0.01710 0.01156 -0.1023 0.7798 0.8251
-1.250 0.3265 0.01727 0.01168 -0.0996 0.7757 0.8358
-1.000 0.3475 0.01739 0.01172 -0.0971 0.7728 0.8502
-0.750 0.3635 0.01759 0.01187 -0.0935 0.7695 0.8669
-0.500 0.3665 0.01787 0.01218 -0.0883 0.7626 0.8804
-0.250 0.3911 0.01782 0.01204 -0.0876 0.7589 0.8899
0.000 0.4221 0.01763 0.01175 -0.0880 0.7563 0.8938
0.250 0.4420 0.01769 0.01178 -0.0868 0.7517 0.8990
0.500 0.4596 0.01780 0.01186 -0.0855 0.7457 0.9044
0.750 0.4888 0.01761 0.01160 -0.0858 0.7423 0.9074
1.000 0.5241 0.01741 0.01131 -0.0873 0.7397 0.9099
1.250 0.5379 0.01760 0.01151 -0.0852 0.7335 0.9147
1.500 0.5630 0.01759 0.01148 -0.0852 0.7285 0.9182
1.750 0.5964 0.01738 0.01120 -0.0863 0.7253 0.9207
2.000 0.6337 0.01717 0.01092 -0.0882 0.7228 0.9228
2.250 0.6414 0.01742 0.01124 -0.0850 0.7148 0.9277
2.500 0.6723 0.01729 0.01108 -0.0858 0.7107 0.9309
2.750 0.7100 0.01707 0.01079 -0.0878 0.7077 0.9334
3.000 0.7248 0.01719 0.01097 -0.0858 0.7010 0.9375
3.250 0.7523 0.01709 0.01087 -0.0859 0.6958 0.9408
3.500 0.7898 0.01683 0.01058 -0.0879 0.6923 0.9433
3.750 0.8088 0.01691 0.01070 -0.0866 0.6858 0.9482
4.000 0.8364 0.01679 0.01059 -0.0868 0.6799 0.9521
4.250 0.8753 0.01650 0.01026 -0.0889 0.6761 0.9547
4.500 0.8928 0.01661 0.01046 -0.0875 0.6686 0.9603
4.750 0.9274 0.01640 0.01026 -0.0889 0.6629 0.9634
5.000 0.9660 0.01618 0.01003 -0.0911 0.6581 0.9666
5.250 0.9879 0.01624 0.01019 -0.0905 0.6495 0.9732
5.500 1.0310 0.01595 0.00986 -0.0935 0.6442 0.9757
5.750 1.0561 0.01603 0.01007 -0.0936 0.6349 0.9824
6.000 1.0987 0.01575 0.00976 -0.0966 0.6284 0.9851
6.250 1.1261 0.01580 0.00993 -0.0972 0.6178 0.9942
6.500 1.1531 0.01570 0.00985 -0.0974 0.6095 1.0000
6.750 1.1738 0.01566 0.00985 -0.0965 0.5997 1.0000
7.000 1.1940 0.01573 0.00999 -0.0956 0.5889 1.0000
7.250 1.2203 0.01573 0.01001 -0.0957 0.5782 1.0000
7.500 1.2470 0.01575 0.01002 -0.0959 0.5664 1.0000
7.750 1.2660 0.01592 0.01026 -0.0948 0.5524 1.0000
8.000 1.2844 0.01610 0.01048 -0.0935 0.5378 1.0000
8.250 1.3022 0.01634 0.01073 -0.0922 0.5222 1.0000
8.500 1.3191 0.01666 0.01104 -0.0907 0.5055 1.0000
8.750 1.3334 0.01708 0.01145 -0.0889 0.4875 1.0000
9.000 1.3446 0.01761 0.01198 -0.0867 0.4685 1.0000
9.250 1.3544 0.01825 0.01258 -0.0843 0.4484 1.0000
9.500 1.3632 0.01899 0.01326 -0.0818 0.4283 1.0000
9.750 1.3693 0.01988 0.01409 -0.0791 0.4075 1.0000
10.000 1.3744 0.02088 0.01506 -0.0764 0.3868 1.0000
10.250 1.3784 0.02201 0.01612 -0.0737 0.3665 1.0000
10.500 1.3815 0.02326 0.01731 -0.0710 0.3466 1.0000
10.750 1.3840 0.02463 0.01864 -0.0685 0.3264 1.0000
11.000 1.3858 0.02612 0.02008 -0.0661 0.3071 1.0000
11.250 1.3868 0.02773 0.02163 -0.0637 0.2886 1.0000
11.500 1.3879 0.02943 0.02329 -0.0616 0.2705 1.0000
11.750 1.3895 0.03119 0.02503 -0.0596 0.2525 1.0000
12.000 1.3906 0.03306 0.02688 -0.0578 0.2351 1.0000
12.250 1.3914 0.03504 0.02883 -0.0561 0.2186 1.0000
12.500 1.3917 0.03713 0.03089 -0.0545 0.2025 1.0000
12.750 1.3920 0.03932 0.03306 -0.0531 0.1871 1.0000
13.000 1.3924 0.04159 0.03532 -0.0518 0.1725 1.0000
13.250 1.3926 0.04396 0.03767 -0.0506 0.1587 1.0000
13.500 1.3925 0.04645 0.04016 -0.0496 0.1455 1.0000
13.750 1.3923 0.04904 0.04275 -0.0487 0.1333 1.0000
14.000 1.3913 0.05180 0.04550 -0.0479 0.1220 1.0000
14.250 1.3889 0.05477 0.04844 -0.0472 0.1119 1.0000
14.500 1.3880 0.05771 0.05140 -0.0467 0.1019 1.0000
14.750 1.3878 0.06064 0.05439 -0.0463 0.0926 1.0000
15.000 1.3854 0.06391 0.05767 -0.0460 0.0847 1.0000
15.250 1.3820 0.06735 0.06111 -0.0459 0.0778 1.0000
15.500 1.3820 0.07053 0.06439 -0.0459 0.0710 1.0000
15.750 1.3773 0.07425 0.06806 -0.0459 0.0657 1.0000
16.000 1.3779 0.07753 0.07149 -0.0462 0.0602 1.0000
16.250 1.3736 0.08132 0.07523 -0.0465 0.0559 1.0000
16.500 1.3740 0.08476 0.07885 -0.0470 0.0517 1.0000
16.750 1.3710 0.08856 0.08264 -0.0477 0.0482 1.0000
17.000 1.3705 0.09214 0.08636 -0.0482 0.0448 1.0000
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Polar data table (+)
Polar graphs
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