EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 200,000 Max Cl/Cd: 56.94 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e857-il-200000.txt Download as CSV file: xf-e857-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 857 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4351 0.11035 0.10659 -0.0621 1.0000 0.0314
-14.250 -0.4407 0.10600 0.10227 -0.0635 1.0000 0.0317
-14.000 -0.6377 0.07077 0.06594 -0.0855 1.0000 0.0271
-13.750 -0.6533 0.06682 0.06194 -0.0862 1.0000 0.0274
-13.500 -0.6831 0.06202 0.05690 -0.0876 1.0000 0.0273
-13.250 -0.6830 0.06012 0.05507 -0.0866 1.0000 0.0277
-13.000 -0.7190 0.05586 0.05049 -0.0868 1.0000 0.0272
-12.750 -0.7146 0.05461 0.04939 -0.0850 1.0000 0.0279
-12.500 -0.7358 0.05209 0.04677 -0.0832 1.0000 0.0279
-12.250 -0.7527 0.05032 0.04495 -0.0811 0.9998 0.0280
-12.000 -0.7291 0.04756 0.04207 -0.0861 0.9945 0.0285
-11.750 -0.7088 0.04489 0.03925 -0.0911 0.9874 0.0297
-11.500 -0.6927 0.04181 0.03586 -0.0956 0.9796 0.0303
-11.250 -0.6784 0.03912 0.03281 -0.0988 0.9702 0.0310
-11.000 -0.6490 0.03704 0.03072 -0.1008 0.9634 0.0320
-10.750 -0.6238 0.03537 0.02902 -0.1023 0.9545 0.0330
-10.500 -0.5920 0.03347 0.02696 -0.1051 0.9489 0.0347
-10.250 -0.5690 0.03172 0.02513 -0.1056 0.9383 0.0362
-10.000 -0.5430 0.03024 0.02370 -0.1067 0.9288 0.0381
-9.750 -0.5114 0.02852 0.02188 -0.1089 0.9226 0.0413
-9.500 -0.4880 0.02717 0.02054 -0.1095 0.9115 0.0444
-9.250 -0.4544 0.02547 0.01884 -0.1119 0.9062 0.0489
-9.000 -0.4300 0.02402 0.01737 -0.1125 0.8938 0.0537
-8.750 -0.3952 0.02260 0.01594 -0.1151 0.8850 0.0608
-8.500 -0.3557 0.02127 0.01461 -0.1186 0.8750 0.0704
-8.250 -0.3139 0.02014 0.01343 -0.1224 0.8626 0.0824
-8.000 -0.2665 0.01887 0.01216 -0.1276 0.8505 0.0978
-7.750 -0.2238 0.01782 0.01107 -0.1317 0.8357 0.1160
-7.500 -0.1932 0.01697 0.01018 -0.1332 0.8180 0.1352
-7.250 -0.1682 0.01623 0.00947 -0.1335 0.8004 0.1581
-7.000 -0.1469 0.01552 0.00882 -0.1330 0.7836 0.1883
-6.750 -0.1276 0.01480 0.00826 -0.1322 0.7680 0.2351
-6.500 -0.1054 0.01440 0.00801 -0.1316 0.7537 0.2969
-6.250 -0.0786 0.01443 0.00800 -0.1314 0.7404 0.3381
-6.000 -0.0547 0.01458 0.00804 -0.1305 0.7263 0.3638
-5.750 -0.0297 0.01479 0.00813 -0.1297 0.7132 0.3829
-5.500 -0.0019 0.01505 0.00825 -0.1294 0.7018 0.3979
-5.250 0.0221 0.01525 0.00835 -0.1284 0.6896 0.4103
-5.000 0.0482 0.01549 0.00839 -0.1279 0.6790 0.4233
-4.750 0.0744 0.01572 0.00861 -0.1272 0.6684 0.4325
-4.500 0.0996 0.01587 0.00857 -0.1266 0.6583 0.4431
-4.250 0.1263 0.01602 0.00870 -0.1261 0.6486 0.4501
-4.000 0.1514 0.01614 0.00869 -0.1255 0.6390 0.4588
-3.750 0.1776 0.01619 0.00863 -0.1250 0.6301 0.4656
-3.500 0.2037 0.01637 0.00877 -0.1245 0.6217 0.4732
-3.250 0.2289 0.01647 0.00872 -0.1239 0.6135 0.4826
-3.000 0.2570 0.01665 0.00887 -0.1237 0.6064 0.4894
-2.750 0.2810 0.01673 0.00890 -0.1229 0.5982 0.4972
-2.500 0.3083 0.01676 0.00878 -0.1228 0.5914 0.5040
-2.250 0.3338 0.01683 0.00885 -0.1223 0.5843 0.5093
-2.000 0.3592 0.01685 0.00880 -0.1218 0.5772 0.5152
-1.750 0.3884 0.01692 0.00865 -0.1222 0.5714 0.5211
-1.500 0.4130 0.01688 0.00864 -0.1216 0.5653 0.5253
-1.250 0.4386 0.01691 0.00865 -0.1211 0.5592 0.5300
-1.000 0.4669 0.01697 0.00859 -0.1213 0.5540 0.5350
-0.750 0.4939 0.01706 0.00856 -0.1213 0.5486 0.5407
-0.500 0.5182 0.01704 0.00857 -0.1207 0.5429 0.5450
-0.250 0.5451 0.01708 0.00858 -0.1205 0.5378 0.5496
0.000 0.5756 0.01724 0.00860 -0.1212 0.5335 0.5549
0.250 0.5996 0.01733 0.00866 -0.1206 0.5288 0.5605
0.500 0.6245 0.01736 0.00873 -0.1201 0.5241 0.5652
0.750 0.6514 0.01744 0.00880 -0.1200 0.5198 0.5703
1.000 0.6811 0.01760 0.00884 -0.1205 0.5158 0.5761
1.250 0.7064 0.01775 0.00896 -0.1202 0.5116 0.5817
1.500 0.7298 0.01781 0.00911 -0.1194 0.5073 0.5867
1.750 0.7558 0.01794 0.00924 -0.1191 0.5033 0.5930
2.000 0.7842 0.01810 0.00932 -0.1194 0.4999 0.5998
2.250 0.8148 0.01832 0.00949 -0.1201 0.4967 0.6054
2.500 0.8370 0.01848 0.00975 -0.1192 0.4931 0.6117
2.750 0.8601 0.01865 0.00994 -0.1185 0.4892 0.6193
3.000 0.8848 0.01876 0.01011 -0.1180 0.4855 0.6261
3.250 0.9121 0.01892 0.01026 -0.1180 0.4823 0.6342
3.500 0.9422 0.01916 0.01045 -0.1187 0.4794 0.6423
3.750 0.9677 0.01946 0.01080 -0.1185 0.4765 0.6506
4.000 0.9878 0.01967 0.01113 -0.1172 0.4733 0.6604
4.250 1.0096 0.01986 0.01142 -0.1162 0.4699 0.6701
4.500 1.0342 0.02003 0.01164 -0.1158 0.4666 0.6813
4.750 1.0613 0.02021 0.01184 -0.1158 0.4637 0.6937
5.000 1.0911 0.02047 0.01211 -0.1165 0.4612 0.7073
5.250 1.1150 0.02083 0.01257 -0.1160 0.4586 0.7231
5.500 1.1314 0.02108 0.01302 -0.1141 0.4557 0.7413
5.750 1.1492 0.02131 0.01342 -0.1124 0.4526 0.7632
6.250 1.1909 0.02154 0.01394 -0.1098 0.4469 0.8375
6.500 1.2320 0.02164 0.01418 -0.1126 0.4442 1.0000
6.750 1.2664 0.02224 0.01467 -0.1145 0.4418 1.0000
7.000 1.2800 0.02271 0.01525 -0.1123 0.4392 1.0000
7.250 1.2950 0.02320 0.01582 -0.1104 0.4362 1.0000
7.500 1.3134 0.02363 0.01631 -0.1091 0.4332 1.0000
7.750 1.3355 0.02400 0.01668 -0.1085 0.4304 1.0000
8.000 1.3630 0.02435 0.01700 -0.1088 0.4279 1.0000
8.250 1.3949 0.02480 0.01740 -0.1099 0.4257 1.0000
8.500 1.4186 0.02548 0.01811 -0.1097 0.4233 1.0000
8.750 1.4232 0.02611 0.01889 -0.1061 0.4205 1.0000
9.000 1.4318 0.02670 0.01959 -0.1031 0.4173 1.0000
9.250 1.4465 0.02721 0.02017 -0.1013 0.4144 1.0000
9.500 1.4662 0.02766 0.02065 -0.1003 0.4120 1.0000
9.750 1.4957 0.02798 0.02096 -0.1010 0.4096 1.0000
10.000 1.5354 0.02846 0.02137 -0.1035 0.4071 1.0000
10.250 1.5294 0.02929 0.02237 -0.0983 0.4043 1.0000
10.500 1.5197 0.03018 0.02342 -0.0925 0.4013 1.0000
10.750 1.5207 0.03092 0.02426 -0.0886 0.3981 1.0000
11.000 1.5361 0.03134 0.02473 -0.0870 0.3951 1.0000
11.250 1.5665 0.03145 0.02482 -0.0877 0.3924 1.0000
11.500 1.6211 0.03147 0.02474 -0.0924 0.3892 1.0000
11.750 1.5840 0.03289 0.02641 -0.0829 0.3860 1.0000
12.000 1.5637 0.03429 0.02797 -0.0767 0.3823 1.0000
12.250 1.5701 0.03494 0.02869 -0.0742 0.3787 1.0000
12.500 1.6026 0.03469 0.02841 -0.0750 0.3756 1.0000
12.750 1.6678 0.03386 0.02744 -0.0802 0.3721 1.0000
13.000 1.6125 0.03649 0.03037 -0.0701 0.3687 1.0000
13.250 1.5728 0.03932 0.03339 -0.0635 0.3644 1.0000
13.500 1.5857 0.03977 0.03388 -0.0622 0.3607 1.0000
13.750 1.6404 0.03826 0.03230 -0.0648 0.3576 1.0000
14.000 1.6578 0.03878 0.03285 -0.0641 0.3540 1.0000
14.250 1.5246 0.04831 0.04278 -0.0528 0.3479 1.0000
14.500 1.5422 0.04858 0.04309 -0.0523 0.3441 1.0000
14.750 1.6169 0.04476 0.03918 -0.0547 0.3414 1.0000
15.000 1.6445 0.04453 0.03895 -0.0548 0.3377 1.0000
15.250 1.3653 0.07279 0.06768 -0.0473 0.3213 1.0000
15.500 1.4230 0.06845 0.06336 -0.0469 0.3205 1.0000
15.750 1.5065 0.06163 0.05652 -0.0469 0.3202 1.0000
16.000 1.4107 0.07479 0.06983 -0.0468 0.3088 1.0000
16.250 1.5008 0.06665 0.06166 -0.0462 0.3092 1.0000
16.500 1.5972 0.05872 0.05363 -0.0465 0.3077 1.0000
16.750 1.4308 0.08001 0.07521 -0.0468 0.2932 1.0000
17.000 1.5156 0.07211 0.06729 -0.0458 0.2928 1.0000
17.250 1.4011 0.08936 0.08469 -0.0481 0.2780 1.0000
17.500 1.4763 0.08213 0.07745 -0.0467 0.2776 1.0000
17.750 1.3907 0.09650 0.09195 -0.0494 0.2634 1.0000
18.000 1.4609 0.08966 0.08509 -0.0478 0.2627 1.0000
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Polar data table (+)
Polar graphs
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