EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.19 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e857-il-1000000.txt Download as CSV file: xf-e857-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7497 0.09831 0.09512 -0.0644 1.0000 0.0084
-17.500 -0.7614 0.09318 0.08991 -0.0666 1.0000 0.0085
-17.250 -0.7728 0.08828 0.08493 -0.0686 1.0000 0.0084
-17.000 -0.7828 0.08370 0.08028 -0.0704 1.0000 0.0083
-16.750 -0.7927 0.07927 0.07577 -0.0720 1.0000 0.0083
-16.500 -0.8001 0.07518 0.07162 -0.0735 1.0000 0.0087
-16.250 -0.8109 0.07093 0.06729 -0.0749 1.0000 0.0086
-16.000 -0.8182 0.06723 0.06353 -0.0760 1.0000 0.0086
-15.750 -0.8283 0.06335 0.05957 -0.0771 1.0000 0.0085
-15.500 -0.8357 0.05993 0.05610 -0.0778 1.0000 0.0087
-15.250 -0.8449 0.05653 0.05264 -0.0783 1.0000 0.0087
-15.000 -0.8359 0.05334 0.04937 -0.0816 0.9989 0.0089
-14.750 -0.8288 0.04966 0.04560 -0.0858 0.9970 0.0090
-14.500 -0.8192 0.04633 0.04220 -0.0898 0.9951 0.0091
-14.250 -0.8031 0.04354 0.03932 -0.0941 0.9936 0.0093
-14.000 -0.7981 0.04018 0.03589 -0.0972 0.9907 0.0092
-13.750 -0.7810 0.03788 0.03352 -0.1003 0.9879 0.0094
-13.500 -0.7649 0.03518 0.03074 -0.1042 0.9856 0.0095
-13.250 -0.7504 0.03190 0.02738 -0.1093 0.9838 0.0097
-13.000 -0.7399 0.02939 0.02480 -0.1115 0.9795 0.0097
-12.750 -0.7269 0.02657 0.02192 -0.1151 0.9749 0.0102
-12.500 -0.7015 0.02442 0.01971 -0.1194 0.9726 0.0105
-12.250 -0.6968 0.02246 0.01769 -0.1194 0.9631 0.0106
-12.000 -0.6972 0.02059 0.01574 -0.1188 0.9502 0.0107
-11.750 -0.6915 0.01948 0.01457 -0.1168 0.9360 0.0110
-11.500 -0.6689 0.01839 0.01340 -0.1174 0.9241 0.0113
-11.250 -0.6294 0.01740 0.01234 -0.1209 0.9143 0.0118
-11.000 -0.5773 0.01601 0.01088 -0.1275 0.9035 0.0128
-10.750 -0.5089 0.01510 0.00986 -0.1368 0.8880 0.0139
-10.500 -0.4441 0.01429 0.00890 -0.1456 0.8587 0.0159
-10.250 -0.4188 0.01398 0.00840 -0.1458 0.8245 0.0171
-10.000 -0.4054 0.01362 0.00792 -0.1436 0.7975 0.0188
-9.750 -0.3901 0.01334 0.00753 -0.1415 0.7755 0.0208
-9.500 -0.3741 0.01306 0.00716 -0.1396 0.7559 0.0231
-9.250 -0.3573 0.01277 0.00680 -0.1378 0.7380 0.0260
-9.000 -0.3394 0.01251 0.00646 -0.1362 0.7212 0.0292
-8.750 -0.3200 0.01225 0.00615 -0.1348 0.7057 0.0328
-8.500 -0.2997 0.01200 0.00586 -0.1335 0.6914 0.0372
-8.250 -0.2787 0.01176 0.00558 -0.1324 0.6787 0.0418
-7.750 -0.2351 0.01129 0.00504 -0.1304 0.6547 0.0534
-7.500 -0.2132 0.01106 0.00479 -0.1294 0.6436 0.0608
-7.250 -0.1902 0.01083 0.00456 -0.1286 0.6326 0.0696
-7.000 -0.1671 0.01062 0.00434 -0.1278 0.6222 0.0795
-6.750 -0.1438 0.01042 0.00413 -0.1270 0.6113 0.0903
-6.500 -0.1196 0.01022 0.00393 -0.1264 0.6018 0.1009
-6.250 -0.0960 0.01003 0.00373 -0.1256 0.5920 0.1136
-6.000 -0.0719 0.00978 0.00352 -0.1251 0.5837 0.1325
-5.750 -0.0488 0.00946 0.00329 -0.1243 0.5749 0.1635
-5.500 -0.0258 0.00912 0.00306 -0.1236 0.5671 0.1995
-5.250 -0.0027 0.00874 0.00284 -0.1229 0.5593 0.2483
-5.000 0.0208 0.00851 0.00270 -0.1222 0.5511 0.2894
-4.750 0.0468 0.00838 0.00262 -0.1219 0.5440 0.3160
-4.500 0.0721 0.00834 0.00257 -0.1213 0.5359 0.3353
-4.250 0.0986 0.00832 0.00253 -0.1210 0.5291 0.3497
-4.000 0.1249 0.00829 0.00251 -0.1206 0.5223 0.3619
-3.750 0.1508 0.00834 0.00248 -0.1202 0.5151 0.3703
-3.500 0.1778 0.00832 0.00247 -0.1199 0.5098 0.3794
-3.250 0.2046 0.00836 0.00246 -0.1196 0.5037 0.3869
-3.000 0.2302 0.00840 0.00246 -0.1191 0.4971 0.3941
-2.750 0.2574 0.00841 0.00246 -0.1189 0.4921 0.3999
-2.500 0.2842 0.00847 0.00245 -0.1186 0.4863 0.4042
-2.250 0.3098 0.00850 0.00246 -0.1181 0.4804 0.4111
-2.000 0.3364 0.00854 0.00248 -0.1178 0.4757 0.4163
-1.750 0.3635 0.00858 0.00248 -0.1176 0.4712 0.4207
-1.500 0.3897 0.00863 0.00250 -0.1172 0.4664 0.4256
-1.250 0.4149 0.00869 0.00254 -0.1166 0.4612 0.4324
-1.000 0.4416 0.00875 0.00258 -0.1163 0.4576 0.4380
-0.750 0.4684 0.00881 0.00261 -0.1161 0.4537 0.4417
-0.500 0.4942 0.00883 0.00262 -0.1156 0.4492 0.4460
-0.250 0.5194 0.00890 0.00266 -0.1151 0.4449 0.4500
0.000 0.5450 0.00898 0.00272 -0.1146 0.4410 0.4535
0.250 0.5720 0.00902 0.00276 -0.1144 0.4384 0.4569
0.500 0.5984 0.00909 0.00280 -0.1141 0.4352 0.4602
0.750 0.6242 0.00916 0.00285 -0.1137 0.4318 0.4636
1.000 0.6491 0.00923 0.00292 -0.1132 0.4281 0.4681
1.250 0.6737 0.00935 0.00302 -0.1125 0.4240 0.4718
1.500 0.7004 0.00939 0.00307 -0.1123 0.4218 0.4757
1.750 0.7268 0.00946 0.00314 -0.1120 0.4193 0.4793
2.000 0.7526 0.00954 0.00321 -0.1117 0.4166 0.4829
2.250 0.7777 0.00960 0.00329 -0.1112 0.4138 0.4879
2.500 0.8021 0.00971 0.00339 -0.1106 0.4107 0.4922
2.750 0.8256 0.00988 0.00352 -0.1098 0.4071 0.4964
3.000 0.8514 0.00995 0.00361 -0.1094 0.4052 0.5003
3.250 0.8769 0.01000 0.00369 -0.1090 0.4031 0.5057
3.500 0.9021 0.01007 0.00379 -0.1086 0.4009 0.5111
3.750 0.9268 0.01016 0.00390 -0.1080 0.3986 0.5162
4.000 0.9511 0.01028 0.00401 -0.1074 0.3962 0.5207
4.250 0.9746 0.01040 0.00415 -0.1067 0.3936 0.5268
4.500 0.9973 0.01058 0.00432 -0.1059 0.3903 0.5334
4.750 1.0219 0.01069 0.00445 -0.1054 0.3884 0.5398
5.000 1.0468 0.01075 0.00457 -0.1049 0.3867 0.5471
5.250 1.0713 0.01084 0.00470 -0.1044 0.3848 0.5550
5.500 1.0953 0.01094 0.00484 -0.1038 0.3828 0.5627
5.750 1.1184 0.01105 0.00500 -0.1031 0.3807 0.5723
6.000 1.1410 0.01119 0.00516 -0.1022 0.3785 0.5823
6.250 1.1627 0.01135 0.00535 -0.1013 0.3760 0.5940
6.500 1.1837 0.01159 0.00560 -0.1002 0.3727 0.6065
7.000 1.2305 0.01178 0.00594 -0.0989 0.3697 0.6369
7.250 1.2531 0.01188 0.00613 -0.0981 0.3679 0.6555
7.500 1.2751 0.01200 0.00633 -0.0973 0.3662 0.6780
7.750 1.2964 0.01211 0.00655 -0.0963 0.3642 0.7059
8.000 1.3164 0.01224 0.00679 -0.0951 0.3620 0.7426
8.250 1.3340 0.01235 0.00706 -0.0934 0.3594 0.7989
8.500 1.3619 0.01236 0.00739 -0.0939 0.3563 1.0000
8.750 1.3834 0.01257 0.00763 -0.0931 0.3546 1.0000
9.000 1.4053 0.01276 0.00785 -0.0923 0.3531 1.0000
9.250 1.4268 0.01295 0.00808 -0.0915 0.3510 1.0000
9.500 1.4478 0.01317 0.00833 -0.0907 0.3488 1.0000
9.750 1.4672 0.01343 0.00860 -0.0895 0.3461 1.0000
10.000 1.4843 0.01378 0.00893 -0.0881 0.3424 1.0000
10.250 1.5008 0.01419 0.00933 -0.0866 0.3387 1.0000
10.500 1.5214 0.01441 0.00961 -0.0858 0.3365 1.0000
10.750 1.5415 0.01467 0.00991 -0.0849 0.3336 1.0000
11.000 1.5597 0.01500 0.01026 -0.0837 0.3305 1.0000
11.250 1.5757 0.01542 0.01069 -0.0823 0.3274 1.0000
11.500 1.5891 0.01598 0.01124 -0.0806 0.3237 1.0000
11.750 1.6072 0.01635 0.01167 -0.0795 0.3213 1.0000
12.000 1.6263 0.01670 0.01206 -0.0787 0.3183 1.0000
12.250 1.6427 0.01716 0.01256 -0.0775 0.3153 1.0000
12.500 1.6561 0.01776 0.01317 -0.0760 0.3113 1.0000
12.750 1.6660 0.01856 0.01397 -0.0741 0.3073 1.0000
13.000 1.6843 0.01900 0.01447 -0.0733 0.3044 1.0000
13.250 1.6993 0.01960 0.01512 -0.0721 0.3006 1.0000
13.500 1.7109 0.02038 0.01592 -0.0706 0.2962 1.0000
13.750 1.7181 0.02144 0.01698 -0.0688 0.2913 1.0000
14.000 1.7332 0.02212 0.01772 -0.0679 0.2871 1.0000
14.250 1.7438 0.02307 0.01870 -0.0665 0.2821 1.0000
14.500 1.7469 0.02450 0.02013 -0.0646 0.2763 1.0000
14.750 1.7588 0.02545 0.02114 -0.0636 0.2712 1.0000
15.000 1.7636 0.02690 0.02261 -0.0621 0.2650 1.0000
15.250 1.7669 0.02851 0.02424 -0.0606 0.2585 1.0000
15.500 1.7693 0.03026 0.02600 -0.0591 0.2509 1.0000
15.750 1.7675 0.03238 0.02814 -0.0576 0.2435 1.0000
16.000 1.7606 0.03499 0.03075 -0.0560 0.2337 1.0000
16.250 1.7556 0.03757 0.03336 -0.0546 0.2247 1.0000
16.500 1.7425 0.04093 0.03672 -0.0532 0.2151 1.0000
16.750 1.7287 0.04450 0.04029 -0.0519 0.2049 1.0000
17.000 1.7122 0.04848 0.04428 -0.0508 0.1946 1.0000
17.250 1.6917 0.05297 0.04879 -0.0499 0.1854 1.0000
17.500 1.6691 0.05783 0.05366 -0.0492 0.1759 1.0000
17.750 1.6536 0.06211 0.05797 -0.0488 0.1682 1.0000
18.000 1.6271 0.06769 0.06356 -0.0486 0.1584 1.0000
18.250 1.6093 0.07248 0.06838 -0.0486 0.1513 1.0000
18.500 1.5918 0.07735 0.07328 -0.0489 0.1446 1.0000
18.750 1.5725 0.08254 0.07849 -0.0493 0.1374 1.0000
19.000 1.5580 0.08728 0.08326 -0.0499 0.1315 1.0000
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Polar data table (+)
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