EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 200,000 Max Cl/Cd: 70.07 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e856-il-200000-n5.txt Download as CSV file: xf-e856-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5058 0.10844 0.10431 -0.0583 1.0000 0.0126
-14.750 -0.5456 0.09614 0.09181 -0.0647 1.0000 0.0126
-14.500 -0.5635 0.08921 0.08478 -0.0680 1.0000 0.0124
-14.250 -0.5838 0.08224 0.07767 -0.0715 1.0000 0.0124
-14.000 -0.6034 0.07587 0.07114 -0.0745 1.0000 0.0124
-13.750 -0.6201 0.07051 0.06564 -0.0768 1.0000 0.0124
-13.500 -0.6343 0.06600 0.06099 -0.0784 1.0000 0.0125
-13.250 -0.6457 0.06215 0.05703 -0.0794 1.0000 0.0124
-13.000 -0.6596 0.05823 0.05296 -0.0802 1.0000 0.0126
-12.750 -0.6709 0.05490 0.04951 -0.0804 1.0000 0.0127
-12.500 -0.6807 0.05207 0.04665 -0.0801 1.0000 0.0128
-12.250 -0.6888 0.04946 0.04396 -0.0797 0.9998 0.0129
-12.000 -0.6736 0.04621 0.04061 -0.0843 0.9958 0.0131
-11.750 -0.6583 0.04324 0.03753 -0.0884 0.9912 0.0132
-11.500 -0.6419 0.04048 0.03465 -0.0923 0.9857 0.0136
-11.250 -0.6268 0.03795 0.03200 -0.0954 0.9789 0.0140
-11.000 -0.6119 0.03557 0.02949 -0.0980 0.9707 0.0143
-10.750 -0.6031 0.03346 0.02726 -0.0990 0.9581 0.0147
-10.500 -0.5980 0.03148 0.02515 -0.0991 0.9424 0.0152
-10.250 -0.5895 0.02963 0.02317 -0.0995 0.9278 0.0156
-10.000 -0.5714 0.02797 0.02144 -0.1005 0.9162 0.0162
-9.750 -0.5472 0.02643 0.01980 -0.1022 0.9063 0.0171
-9.500 -0.5229 0.02510 0.01832 -0.1033 0.8946 0.0183
-9.250 -0.4926 0.02383 0.01697 -0.1055 0.8842 0.0199
-9.000 -0.4561 0.02261 0.01560 -0.1087 0.8741 0.0224
-8.750 -0.4195 0.02144 0.01435 -0.1119 0.8615 0.0248
-8.500 -0.3781 0.02034 0.01312 -0.1160 0.8489 0.0284
-8.250 -0.3379 0.01940 0.01207 -0.1196 0.8345 0.0335
-8.000 -0.3020 0.01860 0.01116 -0.1223 0.8186 0.0392
-7.750 -0.2707 0.01793 0.01038 -0.1238 0.8020 0.0461
-7.500 -0.2429 0.01738 0.00973 -0.1245 0.7859 0.0540
-7.250 -0.2172 0.01688 0.00915 -0.1247 0.7708 0.0632
-7.000 -0.1932 0.01643 0.00863 -0.1245 0.7564 0.0741
-6.750 -0.1700 0.01601 0.00815 -0.1241 0.7423 0.0873
-6.500 -0.1467 0.01561 0.00770 -0.1236 0.7291 0.1032
-6.250 -0.1239 0.01517 0.00725 -0.1232 0.7167 0.1227
-6.000 -0.1008 0.01477 0.00683 -0.1227 0.7049 0.1471
-5.750 -0.0783 0.01431 0.00643 -0.1222 0.6938 0.1796
-5.500 -0.0557 0.01382 0.00604 -0.1217 0.6837 0.2247
-5.250 -0.0331 0.01340 0.00579 -0.1211 0.6733 0.2820
-5.000 -0.0087 0.01322 0.00567 -0.1207 0.6634 0.3285
-4.750 0.0168 0.01318 0.00560 -0.1202 0.6538 0.3605
-4.500 0.0426 0.01319 0.00554 -0.1198 0.6446 0.3830
-4.250 0.0689 0.01323 0.00548 -0.1195 0.6362 0.3998
-4.000 0.0952 0.01326 0.00543 -0.1191 0.6280 0.4133
-3.750 0.1217 0.01332 0.00533 -0.1188 0.6200 0.4251
-3.500 0.1480 0.01336 0.00532 -0.1185 0.6123 0.4353
-3.250 0.1743 0.01341 0.00526 -0.1181 0.6045 0.4452
-3.000 0.2008 0.01349 0.00524 -0.1178 0.5976 0.4561
-2.750 0.2270 0.01355 0.00527 -0.1174 0.5906 0.4664
-2.500 0.2539 0.01365 0.00521 -0.1172 0.5846 0.4761
-2.250 0.2802 0.01365 0.00521 -0.1169 0.5782 0.4816
-2.000 0.3067 0.01369 0.00516 -0.1166 0.5717 0.4869
-1.750 0.3336 0.01375 0.00509 -0.1165 0.5662 0.4925
-1.500 0.3600 0.01375 0.00507 -0.1162 0.5601 0.4968
-1.250 0.3865 0.01379 0.00506 -0.1160 0.5546 0.5013
-0.750 0.4403 0.01391 0.00503 -0.1157 0.5449 0.5117
-0.500 0.4666 0.01394 0.00505 -0.1154 0.5397 0.5156
-0.250 0.4930 0.01401 0.00507 -0.1152 0.5350 0.5204
0.000 0.5197 0.01408 0.00509 -0.1150 0.5304 0.5258
0.250 0.5462 0.01414 0.00513 -0.1148 0.5258 0.5306
0.500 0.5725 0.01421 0.00520 -0.1146 0.5216 0.5351
0.750 0.5992 0.01431 0.00525 -0.1144 0.5178 0.5406
1.000 0.6257 0.01440 0.00531 -0.1143 0.5137 0.5465
1.250 0.6515 0.01446 0.00541 -0.1140 0.5093 0.5511
1.500 0.6776 0.01455 0.00550 -0.1137 0.5052 0.5566
1.750 0.7042 0.01468 0.00558 -0.1135 0.5018 0.5630
2.000 0.7307 0.01479 0.00570 -0.1134 0.4986 0.5687
2.250 0.7562 0.01488 0.00585 -0.1130 0.4947 0.5749
2.500 0.7820 0.01500 0.00597 -0.1127 0.4909 0.5817
2.750 0.8075 0.01510 0.00611 -0.1124 0.4873 0.5881
3.000 0.8339 0.01525 0.00624 -0.1122 0.4842 0.5959
3.250 0.8596 0.01538 0.00642 -0.1120 0.4811 0.6034
3.500 0.8846 0.01550 0.00662 -0.1115 0.4777 0.6115
3.750 0.9096 0.01564 0.00681 -0.1111 0.4743 0.6201
4.000 0.9346 0.01577 0.00699 -0.1107 0.4710 0.6299
4.250 0.9603 0.01593 0.00717 -0.1104 0.4680 0.6403
4.500 0.9856 0.01610 0.00739 -0.1101 0.4651 0.6518
4.750 1.0094 0.01624 0.00765 -0.1095 0.4620 0.6636
5.000 1.0331 0.01639 0.00790 -0.1089 0.4588 0.6771
5.250 1.0568 0.01654 0.00815 -0.1082 0.4557 0.6927
5.500 1.0807 0.01669 0.00836 -0.1076 0.4527 0.7106
5.750 1.1060 0.01687 0.00859 -0.1073 0.4501 0.7312
6.000 1.1272 0.01702 0.00892 -0.1061 0.4472 0.7552
6.250 1.1483 0.01716 0.00923 -0.1049 0.4441 0.7864
6.500 1.1678 0.01725 0.00950 -0.1034 0.4409 0.8335
6.750 1.1958 0.01727 0.00972 -0.1035 0.4378 1.0000
7.000 1.2213 0.01754 0.00997 -0.1034 0.4351 1.0000
7.250 1.2455 0.01784 0.01029 -0.1030 0.4324 1.0000
7.500 1.2646 0.01812 0.01066 -0.1017 0.4289 1.0000
7.750 1.2842 0.01839 0.01100 -0.1004 0.4254 1.0000
8.000 1.3047 0.01867 0.01131 -0.0993 0.4221 1.0000
8.250 1.3272 0.01894 0.01159 -0.0986 0.4189 1.0000
8.500 1.3458 0.01925 0.01195 -0.0972 0.4152 1.0000
8.750 1.3599 0.01956 0.01238 -0.0950 0.4105 1.0000
9.000 1.3757 0.01985 0.01272 -0.0931 0.4059 1.0000
9.250 1.3958 0.02011 0.01295 -0.0920 0.4014 1.0000
9.500 1.4058 0.02050 0.01348 -0.0893 0.3958 1.0000
9.750 1.4182 0.02085 0.01391 -0.0869 0.3900 1.0000
10.000 1.4341 0.02118 0.01422 -0.0852 0.3849 1.0000
10.250 1.4434 0.02168 0.01488 -0.0826 0.3788 1.0000
10.500 1.4551 0.02214 0.01540 -0.0804 0.3730 1.0000
10.750 1.4671 0.02265 0.01595 -0.0783 0.3675 1.0000
11.000 1.4760 0.02328 0.01671 -0.0759 0.3611 1.0000
11.250 1.4859 0.02389 0.01735 -0.0737 0.3549 1.0000
11.500 1.4931 0.02468 0.01827 -0.0714 0.3480 1.0000
11.750 1.5000 0.02552 0.01916 -0.0691 0.3409 1.0000
12.000 1.5055 0.02651 0.02024 -0.0668 0.3333 1.0000
12.250 1.5089 0.02764 0.02141 -0.0645 0.3247 1.0000
12.500 1.5113 0.02895 0.02282 -0.0623 0.3152 1.0000
12.750 1.5115 0.03047 0.02437 -0.0601 0.3054 1.0000
13.000 1.5097 0.03225 0.02620 -0.0579 0.2942 1.0000
13.250 1.5065 0.03428 0.02828 -0.0560 0.2819 1.0000
13.500 1.5003 0.03668 0.03070 -0.0542 0.2687 1.0000
13.750 1.4915 0.03946 0.03348 -0.0525 0.2547 1.0000
14.000 1.4805 0.04261 0.03662 -0.0510 0.2404 1.0000
14.250 1.4675 0.04615 0.04015 -0.0498 0.2263 1.0000
14.500 1.4540 0.04993 0.04392 -0.0489 0.2131 1.0000
14.750 1.4396 0.05400 0.04798 -0.0483 0.2002 1.0000
15.000 1.4257 0.05820 0.05216 -0.0479 0.1885 1.0000
15.250 1.4142 0.06228 0.05625 -0.0478 0.1773 1.0000
15.500 1.4035 0.06640 0.06040 -0.0479 0.1667 1.0000
15.750 1.3929 0.07063 0.06463 -0.0481 0.1569 1.0000
16.000 1.3826 0.07491 0.06892 -0.0485 0.1477 1.0000
16.250 1.3760 0.07884 0.07289 -0.0489 0.1387 1.0000
16.500 1.3678 0.08304 0.07709 -0.0495 0.1307 1.0000
16.750 1.3616 0.08706 0.08114 -0.0502 0.1227 1.0000
17.000 1.3564 0.09100 0.08511 -0.0509 0.1157 1.0000
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Polar data table (+)
Polar graphs
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