EPPLER 857 AIRFOIL (e857-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 857 AIRFOIL (e857-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.08 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e857-il-1000000-n5.txt Download as CSV file: xf-e857-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.7443 0.11360 0.11049 -0.0577 1.0000 0.0059
-18.500 -0.7631 0.10696 0.10375 -0.0608 1.0000 0.0058
-18.250 -0.7845 0.10001 0.09670 -0.0641 1.0000 0.0059
-18.000 -0.7986 0.09328 0.08985 -0.0684 0.9996 0.0058
-17.750 -0.8094 0.08630 0.08275 -0.0740 0.9987 0.0059
-17.500 -0.8153 0.08046 0.07681 -0.0786 0.9977 0.0060
-17.250 -0.8201 0.07497 0.07122 -0.0831 0.9966 0.0060
-17.000 -0.8202 0.07020 0.06635 -0.0873 0.9955 0.0059
-16.750 -0.8185 0.06562 0.06168 -0.0917 0.9945 0.0059
-16.500 -0.8148 0.06138 0.05738 -0.0959 0.9936 0.0063
-16.250 -0.8140 0.05746 0.05337 -0.0991 0.9927 0.0062
-16.000 -0.8148 0.05400 0.04983 -0.1010 0.9912 0.0062
-15.750 -0.8126 0.05067 0.04644 -0.1034 0.9897 0.0062
-15.500 -0.8071 0.04769 0.04339 -0.1058 0.9881 0.0064
-15.250 -0.8007 0.04465 0.04028 -0.1087 0.9866 0.0064
-15.000 -0.7887 0.04209 0.03767 -0.1116 0.9852 0.0065
-14.750 -0.7756 0.03931 0.03482 -0.1152 0.9840 0.0066
-14.500 -0.7599 0.03678 0.03222 -0.1188 0.9830 0.0067
-14.250 -0.7640 0.03464 0.03003 -0.1176 0.9779 0.0068
-14.000 -0.7553 0.03230 0.02763 -0.1194 0.9746 0.0068
-13.750 -0.7380 0.03024 0.02553 -0.1221 0.9721 0.0070
-13.250 -0.7650 0.02676 0.02195 -0.1152 0.9443 0.0070
-13.000 -0.7468 0.02474 0.01986 -0.1177 0.9298 0.0071
-12.750 -0.6964 0.02276 0.01779 -0.1256 0.9165 0.0074
-12.500 -0.6056 0.02051 0.01540 -0.1418 0.8979 0.0081
-12.250 -0.5124 0.01919 0.01380 -0.1574 0.8503 0.0086
-12.000 -0.5028 0.01832 0.01267 -0.1568 0.8021 0.0088
-11.750 -0.5012 0.01746 0.01164 -0.1546 0.7718 0.0091
-11.500 -0.5041 0.01676 0.01079 -0.1510 0.7466 0.0093
-11.250 -0.5035 0.01635 0.01026 -0.1470 0.7278 0.0095
-11.000 -0.4951 0.01590 0.00972 -0.1443 0.7115 0.0099
-10.750 -0.4829 0.01553 0.00926 -0.1421 0.6961 0.0103
-10.500 -0.4689 0.01518 0.00883 -0.1402 0.6808 0.0110
-10.250 -0.4527 0.01486 0.00843 -0.1385 0.6667 0.0115
-10.000 -0.4350 0.01452 0.00803 -0.1370 0.6552 0.0122
-9.750 -0.4169 0.01420 0.00765 -0.1356 0.6443 0.0133
-9.500 -0.3969 0.01392 0.00731 -0.1344 0.6335 0.0143
-9.250 -0.3772 0.01362 0.00696 -0.1332 0.6233 0.0157
-9.000 -0.3562 0.01336 0.00665 -0.1322 0.6123 0.0171
-8.750 -0.3350 0.01309 0.00634 -0.1312 0.6026 0.0191
-8.500 -0.3136 0.01284 0.00604 -0.1302 0.5916 0.0216
-8.250 -0.2909 0.01259 0.00576 -0.1294 0.5834 0.0242
-8.000 -0.2681 0.01236 0.00550 -0.1286 0.5746 0.0274
-7.750 -0.2451 0.01213 0.00524 -0.1278 0.5671 0.0312
-7.500 -0.2215 0.01190 0.00500 -0.1271 0.5592 0.0356
-7.250 -0.1980 0.01170 0.00477 -0.1264 0.5514 0.0401
-7.000 -0.1737 0.01149 0.00454 -0.1259 0.5442 0.0452
-6.750 -0.1498 0.01130 0.00433 -0.1252 0.5356 0.0520
-6.500 -0.1255 0.01108 0.00413 -0.1246 0.5288 0.0599
-6.250 -0.1011 0.01087 0.00393 -0.1241 0.5216 0.0704
-5.750 -0.0514 0.01049 0.00358 -0.1231 0.5095 0.0935
-5.500 -0.0263 0.01032 0.00342 -0.1226 0.5035 0.1042
-5.250 -0.0018 0.01015 0.00326 -0.1221 0.4974 0.1180
-5.000 0.0230 0.00992 0.00309 -0.1216 0.4924 0.1377
-4.750 0.0477 0.00970 0.00293 -0.1211 0.4865 0.1634
-4.500 0.0718 0.00947 0.00277 -0.1205 0.4801 0.1930
-4.250 0.0963 0.00921 0.00261 -0.1200 0.4752 0.2291
-4.000 0.1211 0.00896 0.00248 -0.1195 0.4703 0.2688
-3.750 0.1467 0.00884 0.00241 -0.1191 0.4653 0.2955
-3.500 0.1723 0.00879 0.00237 -0.1187 0.4603 0.3155
-3.250 0.1988 0.00872 0.00234 -0.1184 0.4568 0.3335
-3.000 0.2253 0.00869 0.00232 -0.1181 0.4526 0.3461
-2.750 0.2517 0.00870 0.00230 -0.1177 0.4477 0.3544
-2.250 0.3045 0.00874 0.00230 -0.1171 0.4392 0.3709
-2.000 0.3312 0.00875 0.00230 -0.1168 0.4355 0.3781
-1.750 0.3577 0.00878 0.00231 -0.1164 0.4317 0.3838
-1.500 0.3837 0.00882 0.00233 -0.1161 0.4280 0.3906
-1.250 0.4095 0.00886 0.00236 -0.1156 0.4242 0.3994
-1.000 0.4363 0.00889 0.00238 -0.1153 0.4218 0.4056
-0.750 0.4626 0.00891 0.00241 -0.1150 0.4188 0.4115
-0.500 0.4888 0.00896 0.00244 -0.1146 0.4149 0.4153
-0.250 0.5147 0.00903 0.00248 -0.1142 0.4116 0.4186
0.000 0.5404 0.00911 0.00253 -0.1138 0.4081 0.4213
0.250 0.5665 0.00918 0.00257 -0.1134 0.4057 0.4242
0.500 0.5929 0.00921 0.00262 -0.1131 0.4036 0.4282
0.750 0.6191 0.00927 0.00267 -0.1128 0.4012 0.4319
1.000 0.6451 0.00933 0.00273 -0.1124 0.3984 0.4352
1.250 0.6708 0.00942 0.00280 -0.1120 0.3956 0.4383
1.500 0.6960 0.00952 0.00287 -0.1115 0.3924 0.4412
1.750 0.7210 0.00962 0.00296 -0.1110 0.3892 0.4446
2.000 0.7471 0.00967 0.00303 -0.1106 0.3877 0.4488
2.250 0.7729 0.00973 0.00311 -0.1103 0.3858 0.4524
2.500 0.7983 0.00981 0.00319 -0.1098 0.3837 0.4559
2.750 0.8234 0.00990 0.00328 -0.1093 0.3815 0.4593
3.250 0.8722 0.01010 0.00348 -0.1081 0.3761 0.4672
3.500 0.8961 0.01022 0.00360 -0.1074 0.3734 0.4714
3.750 0.9207 0.01032 0.00372 -0.1069 0.3715 0.4754
4.000 0.9459 0.01041 0.00382 -0.1065 0.3702 0.4791
4.250 0.9708 0.01050 0.00393 -0.1060 0.3685 0.4827
4.500 0.9954 0.01059 0.00405 -0.1055 0.3664 0.4882
4.750 1.0196 0.01069 0.00418 -0.1049 0.3643 0.4935
5.000 1.0433 0.01082 0.00431 -0.1042 0.3619 0.4983
5.500 1.0884 0.01111 0.00463 -0.1025 0.3572 0.5080
5.750 1.1111 0.01125 0.00480 -0.1017 0.3552 0.5141
6.000 1.1351 0.01136 0.00494 -0.1011 0.3539 0.5203
6.250 1.1588 0.01147 0.00510 -0.1005 0.3524 0.5267
6.500 1.1821 0.01159 0.00526 -0.0998 0.3503 0.5344
6.750 1.2049 0.01174 0.00543 -0.0991 0.3482 0.5410
7.000 1.2269 0.01189 0.00563 -0.0982 0.3460 0.5488
7.250 1.2481 0.01206 0.00583 -0.0972 0.3438 0.5575
7.500 1.2690 0.01225 0.00606 -0.0962 0.3418 0.5670
7.750 1.2892 0.01246 0.00630 -0.0951 0.3396 0.5778
8.000 1.3111 0.01262 0.00652 -0.0942 0.3380 0.5894
8.500 1.3541 0.01294 0.00698 -0.0925 0.3343 0.6146
8.750 1.3748 0.01313 0.00723 -0.0915 0.3322 0.6294
9.000 1.3949 0.01333 0.00750 -0.0904 0.3300 0.6465
9.250 1.4132 0.01357 0.00782 -0.0891 0.3273 0.6693
9.500 1.4304 0.01385 0.00817 -0.0876 0.3247 0.6956
9.750 1.4483 0.01408 0.00851 -0.0862 0.3220 0.7289
10.000 1.4666 0.01424 0.00883 -0.0849 0.3186 0.7754
10.250 1.4943 0.01422 0.00922 -0.0856 0.3141 1.0000
10.500 1.5102 0.01465 0.00964 -0.0841 0.3097 1.0000
10.750 1.5264 0.01508 0.01008 -0.0827 0.3058 1.0000
11.000 1.5448 0.01544 0.01047 -0.0816 0.3021 1.0000
11.250 1.5611 0.01589 0.01094 -0.0803 0.2981 1.0000
11.500 1.5749 0.01645 0.01150 -0.0787 0.2939 1.0000
11.750 1.5894 0.01701 0.01207 -0.0772 0.2902 1.0000
12.000 1.6051 0.01753 0.01262 -0.0760 0.2855 1.0000
12.250 1.6190 0.01815 0.01327 -0.0745 0.2816 1.0000
12.500 1.6284 0.01901 0.01412 -0.0726 0.2760 1.0000
12.750 1.6424 0.01967 0.01482 -0.0714 0.2716 1.0000
13.000 1.6525 0.02057 0.01573 -0.0697 0.2655 1.0000
13.250 1.6602 0.02163 0.01679 -0.0679 0.2596 1.0000
13.500 1.6696 0.02265 0.01784 -0.0664 0.2532 1.0000
13.750 1.6723 0.02413 0.01930 -0.0644 0.2456 1.0000
14.000 1.6769 0.02554 0.02073 -0.0628 0.2369 1.0000
14.250 1.6779 0.02727 0.02246 -0.0609 0.2294 1.0000
14.500 1.6782 0.02914 0.02434 -0.0592 0.2206 1.0000
14.750 1.6738 0.03144 0.02663 -0.0574 0.2105 1.0000
15.000 1.6641 0.03427 0.02944 -0.0556 0.1994 1.0000
15.250 1.6570 0.03704 0.03223 -0.0541 0.1908 1.0000
15.500 1.6456 0.04030 0.03549 -0.0526 0.1808 1.0000
15.750 1.6314 0.04392 0.03913 -0.0513 0.1716 1.0000
16.000 1.6142 0.04801 0.04322 -0.0502 0.1621 1.0000
16.250 1.6008 0.05186 0.04710 -0.0495 0.1541 1.0000
16.750 1.5724 0.06006 0.05537 -0.0485 0.1405 1.0000
17.000 1.5559 0.06459 0.05992 -0.0482 0.1344 1.0000
17.250 1.5467 0.06839 0.06378 -0.0482 0.1294 1.0000
17.500 1.5265 0.07355 0.06895 -0.0483 0.1219 1.0000
17.750 1.5181 0.07744 0.07289 -0.0486 0.1169 1.0000
18.000 1.5047 0.08197 0.07745 -0.0490 0.1117 1.0000
18.250 1.4922 0.08652 0.08203 -0.0495 0.1057 1.0000
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