GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 500,000 Max Cl/Cd: 85.11 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe612-il-500000-n5.txt Download as CSV file: xf-goe612-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 612 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6358 0.07125 0.06796 -0.0878 0.9916 0.0283
-14.500 -0.6800 0.05916 0.05563 -0.0989 0.9856 0.0283
-14.250 -0.7005 0.05048 0.04672 -0.1084 0.9807 0.0284
-14.000 -0.7069 0.04382 0.03986 -0.1168 0.9751 0.0284
-13.750 -0.7007 0.03765 0.03345 -0.1268 0.9709 0.0285
-13.500 -0.6887 0.03272 0.02829 -0.1360 0.9645 0.0287
-13.250 -0.6759 0.02959 0.02502 -0.1412 0.9574 0.0290
-13.000 -0.6674 0.02790 0.02322 -0.1419 0.9486 0.0292
-12.500 -0.6552 0.02566 0.02078 -0.1387 0.9314 0.0295
-12.250 -0.6434 0.02473 0.01974 -0.1374 0.9246 0.0297
-12.000 -0.6329 0.02390 0.01883 -0.1355 0.9166 0.0299
-11.750 -0.6184 0.02308 0.01792 -0.1342 0.9102 0.0301
-11.500 -0.6039 0.02234 0.01709 -0.1327 0.9032 0.0303
-11.250 -0.5876 0.02160 0.01625 -0.1313 0.8960 0.0305
-11.000 -0.5700 0.02090 0.01546 -0.1301 0.8893 0.0308
-10.750 -0.5520 0.02023 0.01469 -0.1288 0.8812 0.0311
-10.500 -0.5324 0.01959 0.01394 -0.1278 0.8743 0.0314
-10.250 -0.5128 0.01897 0.01323 -0.1266 0.8661 0.0316
-10.000 -0.4918 0.01839 0.01253 -0.1257 0.8585 0.0319
-9.750 -0.4708 0.01784 0.01189 -0.1247 0.8495 0.0322
-9.500 -0.4487 0.01734 0.01127 -0.1238 0.8405 0.0325
-9.250 -0.4262 0.01690 0.01072 -0.1229 0.8302 0.0328
-9.000 -0.4047 0.01634 0.01008 -0.1219 0.8202 0.0333
-8.750 -0.3825 0.01584 0.00952 -0.1210 0.8096 0.0336
-8.500 -0.3595 0.01543 0.00903 -0.1202 0.7996 0.0340
-8.250 -0.3360 0.01506 0.00858 -0.1194 0.7896 0.0344
-8.000 -0.3121 0.01471 0.00815 -0.1187 0.7796 0.0349
-7.750 -0.2881 0.01439 0.00774 -0.1179 0.7702 0.0353
-7.500 -0.2638 0.01407 0.00735 -0.1172 0.7607 0.0358
-7.250 -0.2394 0.01378 0.00697 -0.1166 0.7526 0.0363
-7.000 -0.2144 0.01350 0.00662 -0.1160 0.7451 0.0368
-6.750 -0.1894 0.01325 0.00628 -0.1153 0.7381 0.0373
-6.500 -0.1642 0.01296 0.00594 -0.1148 0.7319 0.0379
-6.250 -0.1393 0.01267 0.00561 -0.1142 0.7252 0.0386
-5.750 -0.0878 0.01224 0.00509 -0.1132 0.7137 0.0405
-5.500 -0.0616 0.01205 0.00485 -0.1127 0.7084 0.0416
-5.250 -0.0354 0.01188 0.00463 -0.1123 0.7034 0.0426
-5.000 -0.0094 0.01167 0.00438 -0.1118 0.6988 0.0439
-4.750 0.0169 0.01147 0.00417 -0.1114 0.6938 0.0455
-4.500 0.0433 0.01132 0.00398 -0.1110 0.6883 0.0473
-4.000 0.0959 0.01101 0.00362 -0.1101 0.6769 0.0522
-3.750 0.1223 0.01088 0.00346 -0.1097 0.6708 0.0558
-3.500 0.1485 0.01074 0.00330 -0.1092 0.6655 0.0615
-3.250 0.1749 0.01057 0.00317 -0.1088 0.6607 0.0710
-3.000 0.2012 0.01041 0.00308 -0.1084 0.6551 0.0866
-2.750 0.2277 0.01032 0.00299 -0.1080 0.6496 0.0988
-2.500 0.2543 0.01024 0.00291 -0.1076 0.6448 0.1077
-2.250 0.2812 0.01016 0.00284 -0.1073 0.6394 0.1159
-2.000 0.3075 0.01007 0.00277 -0.1068 0.6333 0.1259
-1.750 0.3336 0.01000 0.00270 -0.1064 0.6273 0.1373
-1.500 0.3600 0.00990 0.00265 -0.1060 0.6211 0.1521
-1.250 0.3858 0.00980 0.00260 -0.1054 0.6148 0.1765
-1.000 0.4115 0.00968 0.00258 -0.1049 0.6096 0.2107
-0.750 0.4377 0.00957 0.00258 -0.1045 0.6040 0.2427
-0.500 0.4635 0.00951 0.00259 -0.1040 0.5978 0.2707
-0.250 0.4892 0.00948 0.00260 -0.1035 0.5922 0.2952
0.000 0.5158 0.00945 0.00261 -0.1031 0.5865 0.3121
0.250 0.5417 0.00946 0.00263 -0.1025 0.5798 0.3262
0.500 0.5674 0.00948 0.00265 -0.1020 0.5728 0.3405
0.750 0.5929 0.00949 0.00268 -0.1014 0.5644 0.3546
1.000 0.6179 0.00952 0.00271 -0.1007 0.5563 0.3682
1.250 0.6431 0.00954 0.00275 -0.1000 0.5473 0.3835
1.500 0.6673 0.00958 0.00280 -0.0992 0.5375 0.4028
1.750 0.6905 0.00963 0.00286 -0.0982 0.5248 0.4232
2.000 0.7133 0.00970 0.00293 -0.0971 0.5098 0.4429
2.250 0.7346 0.00980 0.00302 -0.0957 0.4919 0.4632
2.500 0.7545 0.00995 0.00313 -0.0941 0.4714 0.4852
2.750 0.7720 0.01012 0.00328 -0.0921 0.4461 0.5168
3.000 0.7871 0.01030 0.00346 -0.0896 0.4206 0.5614
3.250 0.7966 0.01021 0.00368 -0.0860 0.3978 0.6952
3.500 0.8920 0.01048 0.00431 -0.1008 0.3629 1.0000
3.750 0.9086 0.01078 0.00451 -0.0986 0.3496 1.0000
4.250 0.9407 0.01134 0.00492 -0.0940 0.3277 1.0000
4.500 0.9539 0.01164 0.00514 -0.0912 0.3177 1.0000
4.750 0.9695 0.01190 0.00535 -0.0888 0.3084 1.0000
5.000 0.9845 0.01220 0.00559 -0.0864 0.3010 1.0000
5.250 1.0033 0.01242 0.00579 -0.0847 0.2960 1.0000
5.500 1.0215 0.01267 0.00602 -0.0830 0.2910 1.0000
5.750 1.0386 0.01298 0.00629 -0.0811 0.2860 1.0000
6.000 1.0574 0.01324 0.00655 -0.0795 0.2816 1.0000
6.250 1.0766 0.01351 0.00681 -0.0781 0.2766 1.0000
6.500 1.0943 0.01384 0.00712 -0.0764 0.2712 1.0000
6.750 1.1117 0.01420 0.00745 -0.0748 0.2665 1.0000
7.000 1.1314 0.01448 0.00774 -0.0735 0.2624 1.0000
7.250 1.1501 0.01481 0.00807 -0.0721 0.2578 1.0000
7.500 1.1675 0.01522 0.00845 -0.0706 0.2530 1.0000
7.750 1.1853 0.01561 0.00884 -0.0691 0.2488 1.0000
8.000 1.2043 0.01597 0.00921 -0.0679 0.2442 1.0000
8.250 1.2218 0.01640 0.00964 -0.0665 0.2393 1.0000
8.500 1.2378 0.01692 0.01014 -0.0650 0.2343 1.0000
8.750 1.2564 0.01733 0.01057 -0.0638 0.2300 1.0000
9.000 1.2735 0.01782 0.01107 -0.0625 0.2247 1.0000
9.250 1.2888 0.01842 0.01165 -0.0610 0.2192 1.0000
9.500 1.3058 0.01895 0.01220 -0.0597 0.2140 1.0000
9.750 1.3215 0.01957 0.01281 -0.0584 0.2077 1.0000
10.000 1.3356 0.02029 0.01352 -0.0569 0.2023 1.0000
10.250 1.3517 0.02092 0.01417 -0.0557 0.1963 1.0000
10.500 1.3653 0.02172 0.01495 -0.0543 0.1903 1.0000
10.750 1.3796 0.02249 0.01573 -0.0531 0.1854 1.0000
11.000 1.3931 0.02333 0.01657 -0.0518 0.1791 1.0000
11.250 1.4047 0.02432 0.01755 -0.0504 0.1733 1.0000
11.500 1.4176 0.02524 0.01848 -0.0492 0.1666 1.0000
11.750 1.4274 0.02641 0.01962 -0.0478 0.1602 1.0000
12.000 1.4404 0.02738 0.02062 -0.0467 0.1555 1.0000
12.250 1.4504 0.02858 0.02182 -0.0455 0.1494 1.0000
12.500 1.4608 0.02979 0.02304 -0.0443 0.1458 1.0000
12.750 1.4726 0.03091 0.02420 -0.0433 0.1415 1.0000
13.000 1.4829 0.03218 0.02549 -0.0423 0.1378 1.0000
13.250 1.4913 0.03363 0.02694 -0.0413 0.1339 1.0000
13.500 1.5016 0.03494 0.02830 -0.0404 0.1301 1.0000
13.750 1.5119 0.03627 0.02966 -0.0395 0.1273 1.0000
14.000 1.5198 0.03783 0.03124 -0.0386 0.1237 1.0000
14.250 1.5270 0.03947 0.03292 -0.0377 0.1213 1.0000
14.500 1.5362 0.04097 0.03447 -0.0370 0.1191 1.0000
14.750 1.5454 0.04248 0.03604 -0.0363 0.1169 1.0000
15.000 1.5534 0.04411 0.03772 -0.0356 0.1143 1.0000
15.250 1.5589 0.04601 0.03967 -0.0349 0.1113 1.0000
15.500 1.5623 0.04815 0.04182 -0.0342 0.1076 1.0000
15.750 1.5701 0.04988 0.04363 -0.0337 0.1058 1.0000
16.000 1.5767 0.05175 0.04557 -0.0332 0.1037 1.0000
16.250 1.5807 0.05392 0.04777 -0.0328 0.1006 1.0000
16.500 1.5830 0.05629 0.05020 -0.0323 0.0983 1.0000
16.750 1.5860 0.05862 0.05259 -0.0320 0.0958 1.0000
17.000 1.5897 0.06093 0.05497 -0.0317 0.0919 1.0000
17.250 1.5892 0.06373 0.05779 -0.0315 0.0879 1.0000
17.500 1.5890 0.06652 0.06064 -0.0314 0.0834 1.0000
17.750 1.5860 0.06971 0.06387 -0.0314 0.0784 1.0000
18.000 1.5772 0.07366 0.06783 -0.0315 0.0700 1.0000
18.250 1.5616 0.07855 0.07271 -0.0319 0.0607 1.0000
18.500 1.5376 0.08465 0.07880 -0.0327 0.0492 1.0000
18.750 1.5108 0.09138 0.08555 -0.0339 0.0398 1.0000
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Polar data table (+)
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