EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 500,000 Max Cl/Cd: 79.06 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87151-il-500000-n5.txt Download as CSV file: xf-ste87151-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 871-514 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3007 0.08795 0.08505 -0.1017 0.9075 0.0080
-11.250 -0.3058 0.08197 0.07909 -0.1053 0.9066 0.0080
-11.000 -0.3141 0.07464 0.07178 -0.1106 0.9057 0.0078
-10.750 -0.3355 0.06360 0.06066 -0.1206 0.9044 0.0076
-10.500 -0.3581 0.05677 0.05369 -0.1244 0.9031 0.0075
-10.250 -0.3780 0.05130 0.04807 -0.1258 0.9018 0.0074
-10.000 -0.3959 0.04632 0.04289 -0.1257 0.9002 0.0073
-9.750 -0.4126 0.04142 0.03771 -0.1241 0.8986 0.0071
-9.500 -0.4303 0.03447 0.03025 -0.1213 0.8969 0.0069
-9.250 -0.4386 0.02814 0.02324 -0.1183 0.8954 0.0069
-9.000 -0.4272 0.02530 0.02001 -0.1168 0.8944 0.0070
-8.750 -0.4103 0.02332 0.01772 -0.1158 0.8934 0.0071
-8.500 -0.3906 0.02177 0.01593 -0.1151 0.8927 0.0073
-8.250 -0.3692 0.02047 0.01441 -0.1145 0.8921 0.0075
-8.000 -0.3468 0.01941 0.01317 -0.1140 0.8916 0.0078
-7.750 -0.3238 0.01852 0.01214 -0.1136 0.8910 0.0080
-7.500 -0.3005 0.01778 0.01127 -0.1132 0.8905 0.0083
-7.250 -0.2769 0.01717 0.01056 -0.1128 0.8900 0.0085
-7.000 -0.2544 0.01645 0.00977 -0.1123 0.8895 0.0087
-6.750 -0.2314 0.01592 0.00921 -0.1119 0.8889 0.0091
-6.500 -0.2071 0.01559 0.00886 -0.1117 0.8884 0.0096
-6.250 -0.1831 0.01527 0.00851 -0.1114 0.8876 0.0102
-6.000 -0.1614 0.01496 0.00817 -0.1107 0.8868 0.0107
-5.750 -0.1405 0.01466 0.00784 -0.1098 0.8859 0.0112
-5.500 -0.1202 0.01437 0.00753 -0.1087 0.8847 0.0116
-5.250 -0.1002 0.01410 0.00725 -0.1076 0.8832 0.0122
-5.000 -0.0788 0.01392 0.00707 -0.1068 0.8820 0.0130
-4.750 -0.0567 0.01375 0.00688 -0.1060 0.8808 0.0140
-4.500 -0.0331 0.01352 0.00663 -0.1054 0.8794 0.0153
-4.250 -0.0082 0.01330 0.00642 -0.1052 0.8781 0.0178
-4.000 0.0176 0.01307 0.00619 -0.1051 0.8770 0.0214
-3.750 0.0441 0.01283 0.00595 -0.1051 0.8760 0.0270
-3.500 0.0705 0.01260 0.00576 -0.1052 0.8752 0.0382
-3.250 0.0958 0.01223 0.00559 -0.1052 0.8745 0.0870
-3.000 0.1196 0.01152 0.00537 -0.1053 0.8737 0.2203
-2.750 0.1429 0.01033 0.00504 -0.1059 0.8729 0.4556
-2.500 0.1569 0.00980 0.00547 -0.1037 0.8704 0.6859
-2.250 0.1763 0.01020 0.00589 -0.1020 0.8672 0.7298
-2.000 0.2009 0.01059 0.00626 -0.1011 0.8651 0.7550
-1.750 0.2263 0.01095 0.00660 -0.1004 0.8636 0.7684
-1.500 0.2512 0.01117 0.00685 -0.0996 0.8624 0.7730
-1.250 0.2789 0.01128 0.00694 -0.0995 0.8615 0.7772
-1.000 0.3092 0.01127 0.00689 -0.1002 0.8606 0.7802
-0.750 0.3409 0.01121 0.00678 -0.1012 0.8598 0.7824
-0.500 0.3725 0.01114 0.00668 -0.1022 0.8590 0.7838
-0.250 0.4044 0.01103 0.00655 -0.1032 0.8582 0.7846
0.250 0.4432 0.01118 0.00673 -0.1000 0.8494 0.7869
0.500 0.4755 0.01093 0.00648 -0.1009 0.8472 0.7877
0.750 0.5115 0.01058 0.00611 -0.1026 0.8451 0.7883
1.000 0.5490 0.01020 0.00571 -0.1045 0.8431 0.7890
1.250 0.5606 0.01027 0.00582 -0.1013 0.8349 0.7902
1.500 0.5930 0.00990 0.00545 -0.1022 0.8304 0.7908
1.750 0.6061 0.00989 0.00547 -0.0992 0.8211 0.7921
2.000 0.6182 0.00985 0.00545 -0.0960 0.8098 0.7932
2.250 0.6302 0.01002 0.00563 -0.0931 0.7908 0.7942
2.500 0.6870 0.00869 0.00394 -0.0979 0.7248 0.7941
2.750 0.6961 0.00920 0.00398 -0.0940 0.6443 0.7952
3.000 0.7055 0.00978 0.00430 -0.0906 0.5965 0.7963
3.250 0.7118 0.01054 0.00474 -0.0867 0.5307 0.7972
3.500 0.7215 0.01125 0.00518 -0.0836 0.4742 0.7979
3.750 0.7344 0.01191 0.00558 -0.0813 0.4219 0.7985
4.000 0.7483 0.01255 0.00597 -0.0791 0.3691 0.7991
4.250 0.7630 0.01319 0.00635 -0.0771 0.3152 0.7996
4.500 0.7790 0.01380 0.00673 -0.0754 0.2650 0.8002
4.750 0.7968 0.01435 0.00709 -0.0740 0.2247 0.8009
5.000 0.8154 0.01486 0.00745 -0.0728 0.1900 0.8014
5.250 0.8344 0.01537 0.00780 -0.0717 0.1590 0.8019
5.500 0.8540 0.01585 0.00816 -0.0707 0.1336 0.8024
5.750 0.8740 0.01631 0.00852 -0.0697 0.1138 0.8029
6.000 0.8946 0.01673 0.00888 -0.0688 0.0996 0.8034
6.250 0.9155 0.01712 0.00924 -0.0680 0.0890 0.8039
6.500 0.9365 0.01752 0.00961 -0.0673 0.0811 0.8044
6.750 0.9569 0.01795 0.01002 -0.0664 0.0737 0.8049
7.000 0.9780 0.01833 0.01041 -0.0657 0.0689 0.8054
7.250 0.9985 0.01875 0.01082 -0.0648 0.0643 0.8060
7.500 1.0186 0.01920 0.01128 -0.0640 0.0605 0.8065
7.750 1.0394 0.01959 0.01172 -0.0632 0.0584 0.8070
8.000 1.0595 0.02003 0.01218 -0.0623 0.0560 0.8076
8.250 1.0790 0.02051 0.01267 -0.0614 0.0537 0.8082
8.500 1.0975 0.02105 0.01323 -0.0603 0.0514 0.8090
8.750 1.1163 0.02157 0.01379 -0.0593 0.0497 0.8097
9.000 1.1358 0.02204 0.01432 -0.0584 0.0483 0.8104
9.250 1.1545 0.02256 0.01489 -0.0574 0.0470 0.8109
9.500 1.1726 0.02312 0.01550 -0.0563 0.0456 0.8115
9.750 1.1901 0.02371 0.01613 -0.0552 0.0444 0.8120
10.000 1.2070 0.02435 0.01681 -0.0540 0.0431 0.8126
10.250 1.2223 0.02511 0.01760 -0.0526 0.0419 0.8131
10.500 1.2367 0.02592 0.01847 -0.0511 0.0409 0.8136
10.750 1.2534 0.02655 0.01918 -0.0499 0.0402 0.8141
11.000 1.2698 0.02719 0.01991 -0.0488 0.0394 0.8147
11.250 1.2853 0.02791 0.02071 -0.0475 0.0386 0.8153
11.500 1.3000 0.02867 0.02156 -0.0461 0.0378 0.8159
11.750 1.3151 0.02941 0.02237 -0.0449 0.0367 0.8166
12.000 1.3303 0.03014 0.02314 -0.0437 0.0354 0.8172
12.250 1.3429 0.03106 0.02410 -0.0423 0.0340 0.8179
12.500 1.3542 0.03209 0.02520 -0.0407 0.0330 0.8185
12.750 1.3681 0.03293 0.02615 -0.0394 0.0325 0.8193
13.000 1.3811 0.03386 0.02718 -0.0381 0.0317 0.8200
13.250 1.3937 0.03481 0.02823 -0.0369 0.0309 0.8207
13.500 1.4062 0.03578 0.02930 -0.0356 0.0300 0.8215
13.750 1.4180 0.03682 0.03041 -0.0344 0.0291 0.8223
14.000 1.4286 0.03797 0.03162 -0.0331 0.0283 0.8231
14.250 1.4373 0.03931 0.03302 -0.0317 0.0274 0.8240
14.500 1.4448 0.04077 0.03457 -0.0303 0.0267 0.8248
14.750 1.4550 0.04203 0.03596 -0.0291 0.0260 0.8257
15.000 1.4646 0.04337 0.03741 -0.0280 0.0252 0.8267
15.250 1.4735 0.04478 0.03893 -0.0270 0.0242 0.8277
15.500 1.4824 0.04625 0.04048 -0.0261 0.0231 0.8287
15.750 1.4891 0.04794 0.04223 -0.0251 0.0221 0.8297
16.000 1.4947 0.04978 0.04418 -0.0241 0.0212 0.8306
16.250 1.5013 0.05155 0.04609 -0.0233 0.0200 0.8316
16.500 1.5070 0.05346 0.04809 -0.0226 0.0187 0.8326
16.750 1.5106 0.05564 0.05034 -0.0219 0.0176 0.8337
17.000 1.5125 0.05807 0.05289 -0.0213 0.0167 0.8348
17.250 1.5137 0.06065 0.05560 -0.0209 0.0156 0.8359
17.500 1.5131 0.06354 0.05860 -0.0206 0.0147 0.8371
18.000 1.5065 0.07023 0.06554 -0.0207 0.0131 0.8394
18.250 1.5010 0.07400 0.06944 -0.0210 0.0124 0.8406
18.500 1.4935 0.07818 0.07375 -0.0217 0.0119 0.8418
18.750 1.4840 0.08282 0.07852 -0.0227 0.0115 0.8429
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Polar data table (+)
Polar graphs
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