EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 50,000 Max Cl/Cd: 28.03 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87151-il-50000.txt Download as CSV file: xf-ste87151-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4812 0.11776 0.11138 -0.0098 1.0020 0.3424
-8.250 -0.4902 0.11555 0.10924 -0.0075 1.0020 0.3606
-7.750 -0.4877 0.11041 0.10420 -0.0024 1.0020 0.4029
-7.500 -0.4753 0.10736 0.10116 -0.0001 1.0020 0.4264
-7.250 -0.4648 0.10452 0.09833 0.0023 1.0020 0.4509
-7.000 -0.4586 0.10201 0.09585 0.0049 1.0020 0.4765
-6.750 -0.4672 0.10042 0.09435 0.0091 1.0020 0.5079
-5.250 -0.6251 0.05576 0.04747 -0.0230 1.0020 0.1472
-5.000 -0.6012 0.05133 0.04251 -0.0230 1.0020 0.1299
-4.750 -0.5756 0.04776 0.03824 -0.0228 1.0020 0.1184
-4.500 -0.5488 0.04486 0.03459 -0.0223 1.0020 0.1109
-4.250 -0.5237 0.04235 0.03173 -0.0217 1.0020 0.1079
-4.000 -0.4980 0.04027 0.02925 -0.0210 1.0020 0.1070
-3.750 -0.4729 0.03864 0.02727 -0.0201 1.0020 0.1097
-3.500 -0.4474 0.03726 0.02552 -0.0191 1.0020 0.1128
-3.250 -0.4238 0.03582 0.02413 -0.0177 1.0020 0.1162
-3.000 -0.4004 0.03491 0.02312 -0.0158 1.0020 0.1217
-2.750 -0.1756 0.03660 0.02789 -0.0281 1.0020 0.9980
-2.500 -0.1669 0.03630 0.02730 -0.0258 1.0020 0.9980
-2.250 -0.1581 0.03604 0.02679 -0.0236 1.0020 0.9980
-2.000 -0.1493 0.03582 0.02635 -0.0214 1.0020 0.9980
-1.750 -0.1404 0.03563 0.02597 -0.0192 1.0020 0.9980
-1.500 -0.1315 0.03548 0.02563 -0.0169 1.0020 0.9980
-1.250 -0.1227 0.03535 0.02534 -0.0147 1.0020 0.9980
-1.000 -0.1139 0.03526 0.02511 -0.0124 1.0020 0.9980
-0.750 -0.1052 0.03519 0.02491 -0.0102 1.0020 0.9980
-0.500 -0.0966 0.03514 0.02475 -0.0079 1.0020 0.9980
-0.250 -0.0882 0.03511 0.02462 -0.0057 1.0020 0.9980
0.000 -0.0799 0.03511 0.02451 -0.0034 1.0020 0.9980
0.250 -0.0718 0.03512 0.02444 -0.0011 1.0020 0.9980
0.500 -0.0638 0.03515 0.02440 0.0011 1.0020 0.9980
0.750 -0.0559 0.03520 0.02439 0.0033 1.0020 0.9980
1.000 -0.0482 0.03527 0.02440 0.0055 1.0020 0.9980
1.250 -0.0405 0.03535 0.02444 0.0077 1.0020 0.9980
1.500 -0.0328 0.03546 0.02450 0.0098 1.0020 0.9980
1.750 -0.0251 0.03558 0.02460 0.0119 1.0020 0.9980
2.000 -0.0170 0.03575 0.02474 0.0138 1.0020 0.9980
2.250 -0.0077 0.03599 0.02497 0.0154 1.0020 0.9980
2.500 0.0031 0.03632 0.02529 0.0166 1.0020 0.9980
2.750 0.0154 0.03676 0.02572 0.0175 1.0020 0.9980
3.000 0.0291 0.03731 0.02627 0.0181 1.0020 0.9980
3.250 0.0439 0.03796 0.02693 0.0183 1.0020 0.9980
3.500 0.0595 0.03873 0.02771 0.0183 1.0020 0.9980
3.750 0.0757 0.03959 0.02861 0.0180 1.0020 0.9980
4.000 0.0923 0.04056 0.02961 0.0176 1.0020 0.9980
4.250 0.1090 0.04162 0.03073 0.0170 1.0020 0.9980
4.500 0.1257 0.04279 0.03196 0.0163 1.0020 0.9980
4.750 0.1423 0.04406 0.03330 0.0155 1.0020 0.9980
5.000 0.1635 0.04571 0.03503 0.0136 0.9997 0.9980
5.250 0.3037 0.05119 0.04073 -0.0072 0.9036 0.9980
5.500 0.3481 0.05197 0.04163 -0.0108 0.8671 0.9980
5.750 0.3962 0.05273 0.04255 -0.0147 0.8385 0.9980
6.000 0.4445 0.05303 0.04303 -0.0183 0.8118 0.9980
6.250 0.4834 0.05282 0.04306 -0.0201 0.7839 0.9980
6.500 0.5301 0.05210 0.04256 -0.0222 0.7554 0.9980
6.750 0.5856 0.05027 0.04099 -0.0242 0.7259 0.9980
7.000 0.6584 0.04616 0.03729 -0.0259 0.6960 0.9980
7.250 0.7156 0.04164 0.03313 -0.0249 0.6628 0.9980
7.500 0.7841 0.03502 0.02696 -0.0229 0.6233 0.9980
7.750 0.8392 0.02994 0.02158 -0.0189 0.4986 0.9980
8.000 0.8569 0.03111 0.02130 -0.0151 0.3591 0.9980
8.250 0.8878 0.03308 0.02251 -0.0152 0.2883 0.9980
8.500 0.9428 0.03512 0.02426 -0.0192 0.2438 0.9980
8.750 1.0042 0.03754 0.02654 -0.0246 0.2168 0.9980
9.000 1.0527 0.04014 0.02928 -0.0284 0.2008 0.9980
9.250 1.0851 0.04270 0.03214 -0.0297 0.1911 0.9980
9.500 1.1260 0.04570 0.03514 -0.0325 0.1821 0.9980
9.750 1.1361 0.04810 0.03810 -0.0301 0.1781 0.9980
10.000 1.1498 0.05074 0.04113 -0.0286 0.1737 0.9980
10.250 1.1799 0.05402 0.04446 -0.0299 0.1685 0.9980
10.500 1.1824 0.05717 0.04805 -0.0271 0.1669 0.9980
10.750 1.1766 0.06024 0.05160 -0.0233 0.1658 0.9980
11.000 1.1662 0.06347 0.05525 -0.0193 0.1649 0.9980
11.250 1.1504 0.06677 0.05891 -0.0150 0.1646 0.9980
11.500 1.1311 0.07039 0.06284 -0.0109 0.1648 0.9980
11.750 1.1091 0.07438 0.06709 -0.0072 0.1654 0.9980
12.000 1.0866 0.07881 0.07175 -0.0043 0.1662 0.9980
12.250 1.0669 0.08373 0.07685 -0.0024 0.1672 0.9980
12.500 0.6617 0.11641 0.10967 -0.0019 0.2112 0.9980
12.750 0.6749 0.12077 0.11412 -0.0023 0.2142 0.9980
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Polar data table (+)
Polar graphs
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