GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 200,000 Max Cl/Cd: 73.11 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe574-il-200000-n5.txt Download as CSV file: xf-goe574-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 574 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3147 0.10955 0.10627 -0.0294 1.0000 0.0206
-8.750 -0.3141 0.10675 0.10351 -0.0296 1.0000 0.0213
-8.500 -0.3159 0.10429 0.10111 -0.0304 1.0000 0.0227
-8.250 -0.3113 0.10119 0.09804 -0.0324 0.9990 0.0229
-8.000 -0.2975 0.09688 0.09374 -0.0387 0.9951 0.0232
-7.750 -0.2914 0.08957 0.08644 -0.0442 0.9900 0.0151
-7.500 -0.2789 0.08548 0.08235 -0.0473 0.9852 0.0147
-7.250 -0.2674 0.08147 0.07835 -0.0513 0.9780 0.0144
-7.000 -0.2570 0.07708 0.07397 -0.0551 0.9672 0.0140
-6.750 -0.2526 0.07262 0.06952 -0.0579 0.9479 0.0142
-6.500 -0.2474 0.06850 0.06539 -0.0600 0.9246 0.0143
-6.250 -0.2297 0.06309 0.05989 -0.0652 0.9084 0.0144
-6.000 -0.2030 0.05615 0.05277 -0.0723 0.8944 0.0152
-5.750 -0.1760 0.04974 0.04614 -0.0778 0.8820 0.0153
-5.500 -0.1460 0.04276 0.03884 -0.0829 0.8699 0.0154
-5.250 -0.1161 0.03562 0.03126 -0.0872 0.8579 0.0158
-5.000 -0.0740 0.03349 0.02889 -0.0925 0.8446 0.0171
-4.750 -0.0307 0.03008 0.02505 -0.0973 0.8310 0.0196
-4.500 0.0055 0.02460 0.01876 -0.0999 0.8174 0.0213
-4.250 0.0402 0.02157 0.01485 -0.1013 0.8024 0.0243
-4.000 0.0707 0.01993 0.01291 -0.1026 0.7863 0.0266
-3.750 0.0997 0.01872 0.01134 -0.1029 0.7699 0.0288
-3.500 0.1273 0.01798 0.01022 -0.1028 0.7536 0.0324
-3.250 0.1538 0.01729 0.00915 -0.1023 0.7370 0.0338
-3.000 0.1782 0.01601 0.00763 -0.1017 0.7210 0.0362
-2.750 0.2028 0.01545 0.00690 -0.1011 0.7049 0.0384
-2.500 0.2272 0.01490 0.00617 -0.1002 0.6893 0.0395
-2.250 0.2510 0.01447 0.00558 -0.0993 0.6740 0.0407
-2.000 0.2743 0.01411 0.00507 -0.0983 0.6588 0.0415
-1.750 0.2973 0.01388 0.00470 -0.0972 0.6439 0.0433
-1.250 0.3423 0.01347 0.00405 -0.0949 0.6151 0.0448
-1.000 0.3646 0.01332 0.00376 -0.0938 0.6012 0.0450
-0.750 0.3872 0.01322 0.00353 -0.0926 0.5877 0.0452
-0.500 0.4100 0.01314 0.00333 -0.0916 0.5753 0.0458
-0.250 0.4331 0.01309 0.00316 -0.0906 0.5641 0.0468
0.000 0.4563 0.01307 0.00304 -0.0896 0.5538 0.0493
0.250 0.4796 0.01305 0.00297 -0.0886 0.5442 0.0543
0.500 0.5012 0.01281 0.00297 -0.0875 0.5356 0.1433
0.750 0.5150 0.01193 0.00306 -0.0851 0.5284 0.4910
1.250 0.7107 0.01186 0.00371 -0.1167 0.5070 1.0000
1.500 0.7332 0.01200 0.00377 -0.1157 0.5011 1.0000
1.750 0.7560 0.01215 0.00385 -0.1147 0.4962 1.0000
2.000 0.7790 0.01229 0.00395 -0.1138 0.4912 1.0000
2.250 0.8018 0.01244 0.00406 -0.1129 0.4869 1.0000
2.500 0.8248 0.01262 0.00419 -0.1120 0.4832 1.0000
2.750 0.8481 0.01276 0.00434 -0.1112 0.4792 1.0000
3.000 0.8712 0.01293 0.00450 -0.1103 0.4755 1.0000
3.250 0.8942 0.01311 0.00468 -0.1095 0.4719 1.0000
3.500 0.9175 0.01331 0.00486 -0.1087 0.4688 1.0000
3.750 0.9405 0.01348 0.00508 -0.1078 0.4652 1.0000
4.000 0.9637 0.01366 0.00533 -0.1070 0.4621 1.0000
4.250 0.9867 0.01385 0.00556 -0.1061 0.4588 1.0000
4.750 1.0277 0.01421 0.00600 -0.1033 0.4457 1.0000
5.000 1.0435 0.01436 0.00617 -0.1009 0.4327 1.0000
5.250 1.0596 0.01453 0.00635 -0.0985 0.4202 1.0000
5.500 1.0732 0.01468 0.00651 -0.0956 0.4029 1.0000
5.750 1.0862 0.01487 0.00668 -0.0926 0.3834 1.0000
6.000 1.0985 0.01509 0.00689 -0.0895 0.3552 1.0000
6.250 1.0992 0.01572 0.00715 -0.0842 0.2764 1.0000
6.500 1.0804 0.01756 0.00826 -0.0757 0.1657 1.0000
6.750 1.0565 0.01963 0.00966 -0.0666 0.0360 1.0000
7.000 1.0621 0.02042 0.01043 -0.0626 0.0233 1.0000
7.250 1.0711 0.02109 0.01120 -0.0593 0.0200 1.0000
7.500 1.0778 0.02191 0.01216 -0.0557 0.0170 1.0000
7.750 1.0870 0.02262 0.01302 -0.0527 0.0160 1.0000
8.000 1.0943 0.02346 0.01403 -0.0494 0.0152 1.0000
8.250 1.0994 0.02444 0.01517 -0.0459 0.0145 1.0000
8.500 1.1025 0.02556 0.01645 -0.0425 0.0141 1.0000
8.750 1.1039 0.02683 0.01789 -0.0390 0.0132 1.0000
9.000 1.1029 0.02835 0.01953 -0.0356 0.0125 1.0000
9.250 1.1011 0.03005 0.02133 -0.0327 0.0114 1.0000
9.500 1.0975 0.03205 0.02344 -0.0299 0.0111 1.0000
9.750 1.0905 0.03455 0.02604 -0.0274 0.0107 1.0000
10.000 1.0848 0.03714 0.02874 -0.0252 0.0105 1.0000
10.250 1.0814 0.03967 0.03135 -0.0234 0.0103 1.0000
10.500 1.0786 0.04220 0.03395 -0.0215 0.0101 1.0000
10.750 1.0795 0.04446 0.03625 -0.0194 0.0099 1.0000
11.000 1.0870 0.04621 0.03805 -0.0176 0.0096 1.0000
11.250 1.0970 0.04776 0.03969 -0.0162 0.0094 1.0000
11.500 1.1056 0.04941 0.04147 -0.0152 0.0088 1.0000
11.750 1.1160 0.05101 0.04317 -0.0139 0.0084 1.0000
12.000 1.1259 0.05270 0.04502 -0.0127 0.0078 1.0000
12.250 1.1389 0.05434 0.04678 -0.0113 0.0077 1.0000
12.500 1.1501 0.05623 0.04881 -0.0100 0.0075 1.0000
12.750 1.1605 0.05835 0.05110 -0.0087 0.0073 1.0000
13.000 1.1684 0.06079 0.05373 -0.0076 0.0072 1.0000
13.250 1.1734 0.06347 0.05661 -0.0066 0.0072 1.0000
13.500 1.1747 0.06645 0.05979 -0.0057 0.0071 1.0000
13.750 1.1731 0.06981 0.06337 -0.0050 0.0071 1.0000
14.000 1.1685 0.07349 0.06729 -0.0046 0.0072 1.0000
14.250 1.1612 0.07745 0.07147 -0.0045 0.0072 1.0000
14.500 1.1517 0.08175 0.07599 -0.0046 0.0072 1.0000
14.750 1.1408 0.08632 0.08077 -0.0052 0.0073 1.0000
15.000 1.1277 0.09135 0.08603 -0.0061 0.0073 1.0000
15.250 1.1144 0.09648 0.09135 -0.0075 0.0074 1.0000
15.500 1.0998 0.10205 0.09713 -0.0093 0.0075 1.0000
15.750 1.0859 0.10768 0.10293 -0.0114 0.0076 1.0000
16.000 1.0689 0.11420 0.10964 -0.0142 0.0077 1.0000
16.250 1.0534 0.12068 0.11629 -0.0173 0.0077 1.0000
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