GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 100,000 Max Cl/Cd: 45.86 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe553-il-100000.txt Download as CSV file: xf-goe553-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2517 0.10345 0.09864 -0.0377 1.0000 0.1196
-9.000 -0.2805 0.10289 0.09825 -0.0404 1.0000 0.1231
-8.750 -0.3204 0.10300 0.09860 -0.0410 1.0000 0.1238
-8.500 -0.2740 0.09642 0.09195 -0.0374 1.0000 0.1266
-8.250 -0.2685 0.09453 0.09014 -0.0347 1.0000 0.1294
-8.000 -0.2855 0.09410 0.08988 -0.0307 1.0000 0.1311
-7.750 -0.2966 0.09333 0.08925 -0.0305 0.9953 0.1346
-7.500 -0.2881 0.08764 0.08358 -0.0448 0.9769 0.1418
-7.250 -0.2431 0.08396 0.07986 -0.0456 0.9724 0.1487
-7.000 -0.2285 0.07768 0.07357 -0.0609 0.9536 0.1587
-6.750 -0.1919 0.07472 0.07058 -0.0607 0.9456 0.1647
-6.500 -0.1689 0.06895 0.06477 -0.0727 0.9316 0.1768
-6.250 -0.1446 0.06366 0.05938 -0.0838 0.9182 0.1924
-6.000 -0.1145 0.05983 0.05547 -0.0895 0.9086 0.2096
-5.750 -0.0869 0.05792 0.05354 -0.0891 0.8962 0.2226
-5.500 -0.0597 0.05517 0.05077 -0.0894 0.8863 0.2340
-5.250 -0.0442 0.03739 0.03119 -0.1126 0.8692 0.1269
-5.000 -0.0142 0.03310 0.02606 -0.1138 0.8585 0.1059
-4.750 0.0118 0.03079 0.02345 -0.1140 0.8473 0.1035
-4.500 0.0434 0.02879 0.02104 -0.1146 0.8387 0.1033
-4.250 0.0682 0.02730 0.01923 -0.1141 0.8269 0.1025
-4.000 0.0980 0.02579 0.01737 -0.1140 0.8179 0.1017
-3.750 0.1249 0.02467 0.01600 -0.1134 0.8073 0.1020
-3.500 0.1524 0.02372 0.01485 -0.1129 0.7974 0.1033
-3.250 0.1812 0.02297 0.01388 -0.1124 0.7881 0.1067
-3.000 0.2069 0.02224 0.01306 -0.1117 0.7777 0.1098
-2.750 0.2353 0.02132 0.01217 -0.1112 0.7694 0.1138
-2.500 0.2594 0.02086 0.01173 -0.1102 0.7586 0.1188
-2.250 0.2876 0.02018 0.01103 -0.1096 0.7510 0.1271
-2.000 0.3104 0.01985 0.01077 -0.1086 0.7399 0.1409
-1.750 0.3369 0.01903 0.01016 -0.1080 0.7320 0.1798
-1.500 0.3512 0.01787 0.01064 -0.1053 0.7220 0.5964
-1.250 0.3737 0.01804 0.01081 -0.1029 0.7140 0.6610
-1.000 0.3931 0.01822 0.01104 -0.1004 0.7039 0.7065
-0.750 0.4138 0.01831 0.01112 -0.0979 0.6959 0.7513
-0.500 0.4290 0.01832 0.01124 -0.0942 0.6862 0.7982
-0.250 0.4458 0.01820 0.01115 -0.0905 0.6788 0.8464
0.000 0.4647 0.01811 0.01115 -0.0879 0.6690 0.8909
0.250 0.5066 0.01803 0.01097 -0.0898 0.6605 0.9382
0.500 0.5646 0.01808 0.01088 -0.0961 0.6493 1.0000
0.750 0.5883 0.01843 0.01106 -0.0966 0.6403 1.0000
1.000 0.6175 0.01872 0.01117 -0.0975 0.6315 1.0000
1.250 0.6455 0.01912 0.01142 -0.0981 0.6228 1.0000
1.500 0.6739 0.01943 0.01157 -0.0984 0.6140 1.0000
1.750 0.7011 0.01982 0.01184 -0.0985 0.6056 1.0000
2.000 0.7280 0.02017 0.01208 -0.0984 0.5968 1.0000
2.250 0.7559 0.02055 0.01233 -0.0985 0.5898 1.0000
2.500 0.7801 0.02104 0.01279 -0.0981 0.5809 1.0000
2.750 0.8106 0.02126 0.01283 -0.0982 0.5751 1.0000
3.000 0.8316 0.02188 0.01352 -0.0975 0.5654 1.0000
3.250 0.8612 0.02204 0.01353 -0.0975 0.5589 1.0000
3.500 0.8832 0.02266 0.01418 -0.0968 0.5504 1.0000
3.750 0.9108 0.02288 0.01433 -0.0965 0.5434 1.0000
4.000 0.9354 0.02329 0.01471 -0.0960 0.5357 1.0000
4.250 0.9611 0.02351 0.01489 -0.0955 0.5276 1.0000
4.500 0.9884 0.02373 0.01506 -0.0952 0.5209 1.0000
4.750 1.0107 0.02419 0.01556 -0.0945 0.5125 1.0000
5.000 1.0426 0.02412 0.01533 -0.0946 0.5069 1.0000
5.250 1.0606 0.02477 0.01613 -0.0933 0.4975 1.0000
5.500 1.0908 0.02478 0.01602 -0.0934 0.4916 1.0000
5.750 1.1104 0.02550 0.01686 -0.0923 0.4841 1.0000
6.000 1.1363 0.02581 0.01717 -0.0920 0.4777 1.0000
6.250 1.1648 0.02606 0.01737 -0.0919 0.4724 1.0000
6.500 1.1821 0.02687 0.01833 -0.0906 0.4644 1.0000
6.750 1.2127 0.02691 0.01828 -0.0907 0.4587 1.0000
7.000 1.2298 0.02773 0.01927 -0.0894 0.4509 1.0000
7.250 1.2569 0.02791 0.01943 -0.0890 0.4440 1.0000
7.500 1.2791 0.02845 0.02003 -0.0882 0.4369 1.0000
7.750 1.3012 0.02889 0.02054 -0.0874 0.4290 1.0000
8.000 1.3287 0.02918 0.02080 -0.0872 0.4224 1.0000
8.250 1.3448 0.02995 0.02173 -0.0857 0.4138 1.0000
8.500 1.3772 0.03003 0.02171 -0.0860 0.4073 1.0000
8.750 1.3875 0.03107 0.02298 -0.0838 0.3980 1.0000
9.000 1.4212 0.03113 0.02291 -0.0844 0.3911 1.0000
9.250 1.4291 0.03221 0.02424 -0.0818 0.3814 1.0000
9.500 1.4563 0.03241 0.02440 -0.0815 0.3729 1.0000
9.750 1.4717 0.03298 0.02507 -0.0798 0.3632 1.0000
10.000 1.4889 0.03355 0.02569 -0.0783 0.3538 1.0000
10.250 1.5162 0.03348 0.02554 -0.0780 0.3446 1.0000
10.500 1.5215 0.03457 0.02684 -0.0752 0.3356 1.0000
10.750 1.5537 0.03452 0.02665 -0.0756 0.3277 1.0000
11.000 1.5517 0.03599 0.02841 -0.0720 0.3200 1.0000
11.250 1.5804 0.03602 0.02835 -0.0720 0.3124 1.0000
11.500 1.5778 0.03742 0.03000 -0.0684 0.3053 1.0000
11.750 1.5963 0.03779 0.03038 -0.0672 0.2981 1.0000
12.000 1.5997 0.03881 0.03153 -0.0643 0.2916 1.0000
12.250 1.5981 0.03981 0.03267 -0.0609 0.2850 1.0000
12.500 1.6140 0.04016 0.03300 -0.0594 0.2778 1.0000
12.750 1.5989 0.04206 0.03513 -0.0553 0.2721 1.0000
13.000 1.6243 0.04183 0.03480 -0.0548 0.2641 1.0000
13.250 1.5994 0.04463 0.03789 -0.0509 0.2591 1.0000
13.500 1.6144 0.04480 0.03801 -0.0496 0.2506 1.0000
13.750 1.5926 0.04795 0.04142 -0.0471 0.2451 1.0000
14.000 1.5983 0.04885 0.04230 -0.0458 0.2362 1.0000
14.250 1.5759 0.05266 0.04634 -0.0444 0.2298 1.0000
14.500 1.5793 0.05395 0.04756 -0.0435 0.2196 1.0000
14.750 1.5526 0.05885 0.05270 -0.0432 0.2124 1.0000
15.000 1.1324 0.13551 0.12976 -0.0737 0.2091 1.0000
15.250 1.2234 0.11924 0.11371 -0.0649 0.2084 1.0000
15.500 1.2020 0.12686 0.12138 -0.0681 0.1957 1.0000
15.750 1.5029 0.07414 0.06796 -0.0440 0.1677 1.0000
16.000 1.4882 0.07897 0.07280 -0.0448 0.1569 1.0000
16.250 1.4796 0.08306 0.07683 -0.0455 0.1466 1.0000
16.500 1.4697 0.08753 0.08129 -0.0466 0.1377 1.0000
16.750 1.4518 0.09361 0.08753 -0.0486 0.1310 1.0000
17.000 1.4526 0.09657 0.09037 -0.0493 0.1233 1.0000
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