GOE 366 AIRFOIL (goe366-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 366 AIRFOIL (goe366-il) Reynolds number: 200,000 Max Cl/Cd: 82.6 at α=-0.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe366-il-200000.txt Download as CSV file: xf-goe366-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 366 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 0.1181 0.08855 0.08500 -0.1060 0.9337 0.0337
-9.250 0.1317 0.08509 0.08152 -0.1081 0.9302 0.0343
-9.000 0.0386 0.09762 0.09392 -0.1026 0.9475 0.0331
-8.750 0.0607 0.09371 0.09000 -0.1052 0.9448 0.0335
-8.500 0.0719 0.09107 0.08736 -0.1063 0.9356 0.0340
-8.250 0.0889 0.08794 0.08421 -0.1092 0.9306 0.0348
-8.000 0.0975 0.08555 0.08181 -0.1103 0.9206 0.0354
-7.750 0.1103 0.08274 0.07898 -0.1126 0.9140 0.0361
-7.500 0.1155 0.08069 0.07693 -0.1137 0.9034 0.0366
-7.250 0.1212 0.07862 0.07482 -0.1177 0.8954 0.0371
-7.000 0.1294 0.07640 0.07256 -0.1259 0.8836 0.0373
-6.750 0.1424 0.07321 0.06938 -0.1229 0.8797 0.0376
-6.500 0.1523 0.07086 0.06704 -0.1220 0.8725 0.0379
-6.250 0.1652 0.06842 0.06458 -0.1230 0.8658 0.0385
-6.000 0.1828 0.06572 0.06182 -0.1257 0.8610 0.0392
-5.750 0.1951 0.06350 0.05960 -0.1276 0.8522 0.0401
-5.500 0.2160 0.06066 0.05668 -0.1317 0.8463 0.0413
-5.250 0.2467 0.05730 0.05313 -0.1408 0.8392 0.0426
-5.000 0.2577 0.05497 0.05084 -0.1391 0.8327 0.0431
-4.750 0.2778 0.05256 0.04837 -0.1400 0.8278 0.0441
-4.500 0.2971 0.05041 0.04617 -0.1414 0.8204 0.0455
-4.250 0.3406 0.04772 0.04303 -0.1490 0.8138 0.0484
-4.000 0.3582 0.04473 0.04009 -0.1489 0.8092 0.0489
-3.750 0.3734 0.04290 0.03829 -0.1482 0.8007 0.0498
-3.500 0.3996 0.04078 0.03605 -0.1496 0.7949 0.0517
-3.250 0.4352 0.03875 0.03361 -0.1524 0.7877 0.0556
-3.000 0.4547 0.03651 0.03142 -0.1524 0.7803 0.0566
-2.750 0.4805 0.03477 0.02957 -0.1531 0.7738 0.0591
-2.500 0.5113 0.03315 0.02761 -0.1541 0.7651 0.0642
-2.000 0.5655 0.03035 0.02441 -0.1548 0.7487 0.0738
-1.750 0.5911 0.02841 0.02248 -0.1555 0.7415 0.0769
-1.500 0.6173 0.02748 0.02129 -0.1552 0.7307 0.0858
-1.250 0.6434 0.02605 0.01981 -0.1556 0.7221 0.0904
-1.000 0.6404 0.01048 0.00437 -0.1462 0.6916 0.1019
-0.750 0.6651 0.00986 0.00357 -0.1460 0.6803 0.1149
-0.500 0.6918 0.00915 0.00268 -0.1463 0.6704 0.1311
-0.250 0.7137 0.00864 0.00214 -0.1458 0.6575 0.1496
0.000 0.7693 0.02137 0.01452 -0.1545 0.6650 0.1716
0.250 0.7938 0.02049 0.01352 -0.1545 0.6535 0.2173
0.500 0.8156 0.01947 0.01254 -0.1538 0.6396 0.2555
0.750 0.8398 0.01860 0.01161 -0.1532 0.6261 0.2896
1.000 0.8671 0.01806 0.01090 -0.1526 0.6131 0.2991
1.500 0.9363 0.01749 0.00897 -0.1493 0.5896 0.0819
1.750 0.9622 0.01741 0.00864 -0.1483 0.5779 0.0729
2.000 0.9876 0.01685 0.00802 -0.1477 0.5676 0.0699
2.250 1.0127 0.01666 0.00773 -0.1470 0.5569 0.0674
2.500 1.0376 0.01658 0.00758 -0.1464 0.5470 0.0661
2.750 1.0637 0.01657 0.00748 -0.1461 0.5381 0.0667
3.000 1.0883 0.01663 0.00755 -0.1456 0.5293 0.0698
3.250 1.1148 0.01675 0.00756 -0.1454 0.5215 0.0712
3.500 1.1396 0.01692 0.00768 -0.1449 0.5135 0.0728
3.750 1.1652 0.01709 0.00777 -0.1445 0.5059 0.0772
4.000 1.1911 0.01734 0.00796 -0.1443 0.4989 0.0882
4.250 1.2104 0.01613 0.00833 -0.1427 0.4923 1.0000
4.500 1.2375 0.01653 0.00852 -0.1426 0.4862 1.0000
4.750 1.2613 0.01689 0.00884 -0.1420 0.4800 1.0000
5.000 1.2852 0.01722 0.00911 -0.1415 0.4736 1.0000
5.250 1.3127 0.01765 0.00937 -0.1416 0.4681 1.0000
5.500 1.3345 0.01800 0.00976 -0.1408 0.4622 1.0000
5.750 1.3582 0.01835 0.01009 -0.1402 0.4566 1.0000
6.000 1.3848 0.01876 0.01040 -0.1403 0.4518 1.0000
6.250 1.4084 0.01919 0.01084 -0.1398 0.4468 1.0000
6.500 1.4302 0.01956 0.01125 -0.1390 0.4415 1.0000
6.750 1.4547 0.01993 0.01159 -0.1386 0.4367 1.0000
7.000 1.4821 0.02041 0.01199 -0.1389 0.4322 1.0000
7.250 1.5004 0.02080 0.01249 -0.1375 0.4271 1.0000
7.500 1.5222 0.02118 0.01288 -0.1367 0.4221 1.0000
7.750 1.5477 0.02157 0.01321 -0.1366 0.4175 1.0000
8.000 1.5678 0.02204 0.01374 -0.1356 0.4126 1.0000
8.250 1.5860 0.02244 0.01422 -0.1342 0.4075 1.0000
8.500 1.6083 0.02282 0.01462 -0.1335 0.4031 1.0000
8.750 1.6375 0.02332 0.01502 -0.1342 0.3990 1.0000
9.000 1.6500 0.02380 0.01567 -0.1319 0.3946 1.0000
9.250 1.6665 0.02423 0.01618 -0.1303 0.3898 1.0000
9.500 1.6878 0.02460 0.01656 -0.1295 0.3854 1.0000
9.750 1.7129 0.02513 0.01706 -0.1295 0.3813 1.0000
10.000 1.7215 0.02566 0.01777 -0.1266 0.3772 1.0000
10.250 1.7349 0.02614 0.01833 -0.1245 0.3728 1.0000
10.500 1.7544 0.02653 0.01873 -0.1235 0.3685 1.0000
10.750 1.7724 0.02708 0.01930 -0.1223 0.3640 1.0000
11.000 1.7755 0.02773 0.02012 -0.1187 0.3592 1.0000
11.250 1.7867 0.02823 0.02067 -0.1164 0.3542 1.0000
11.500 1.8086 0.02862 0.02100 -0.1159 0.3490 1.0000
11.750 1.8057 0.02955 0.02215 -0.1118 0.3443 1.0000
12.000 1.8118 0.03028 0.02297 -0.1091 0.3389 1.0000
12.250 1.8302 0.03070 0.02331 -0.1082 0.3334 1.0000
12.500 1.8258 0.03194 0.02479 -0.1044 0.3283 1.0000
12.750 1.8289 0.03295 0.02590 -0.1018 0.3226 1.0000
13.000 1.8429 0.03358 0.02647 -0.1005 0.3170 1.0000
13.250 1.8371 0.03522 0.02835 -0.0972 0.3114 1.0000
13.500 1.8392 0.03651 0.02974 -0.0949 0.3055 1.0000
13.750 1.8445 0.03773 0.03099 -0.0930 0.2996 1.0000
14.000 1.8395 0.03969 0.03313 -0.0905 0.2929 1.0000
14.250 1.8439 0.04102 0.03444 -0.0888 0.2863 1.0000
14.500 1.8367 0.04348 0.03712 -0.0866 0.2792 1.0000
14.750 1.8363 0.04544 0.03911 -0.0850 0.2720 1.0000
15.000 1.8310 0.04807 0.04192 -0.0834 0.2642 1.0000
15.250 1.8280 0.05051 0.04437 -0.0820 0.2564 1.0000
15.500 1.8203 0.05370 0.04774 -0.0808 0.2472 1.0000
15.750 1.8131 0.05689 0.05099 -0.0797 0.2383 1.0000
16.000 1.8027 0.06059 0.05475 -0.0787 0.2283 1.0000
16.250 1.7907 0.06465 0.05891 -0.0780 0.2176 1.0000
16.500 1.7767 0.06907 0.06338 -0.0774 0.2069 1.0000
16.750 1.7603 0.07394 0.06827 -0.0771 0.1963 1.0000
17.000 1.7427 0.07910 0.07344 -0.0770 0.1861 1.0000
17.250 1.7270 0.08415 0.07855 -0.0771 0.1767 1.0000
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