GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 382 AIRFOIL (goe382-il) Reynolds number: 500,000 Max Cl/Cd: 86.98 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe382-il-500000.txt Download as CSV file: xf-goe382-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 382 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1080 0.11776 0.11493 -0.0705 0.8383 0.0397
-12.250 -0.1009 0.11517 0.11227 -0.0712 0.8227 0.0403
-12.000 -0.1292 0.10506 0.10211 -0.0786 0.8140 0.0435
-11.750 -0.1176 0.10335 0.10032 -0.0782 0.7971 0.0437
-11.500 -0.1063 0.10159 0.09847 -0.0783 0.7804 0.0440
-11.250 -0.0360 0.08696 0.08369 -0.0896 0.7254 0.0486
-11.000 -0.0242 0.08523 0.08189 -0.0890 0.7151 0.0489
-10.750 -0.0140 0.08323 0.07985 -0.0890 0.7058 0.0491
-10.500 -0.0049 0.08111 0.07766 -0.0892 0.6982 0.0495
-10.250 0.0025 0.07862 0.07516 -0.0897 0.6911 0.0500
-10.000 -0.0947 0.07930 0.07584 -0.0903 0.7099 0.0497
-9.750 -0.3742 0.03225 0.02682 -0.1128 0.7162 0.0388
-9.500 -0.3604 0.03057 0.02486 -0.1117 0.7073 0.0387
-9.250 -0.3431 0.02934 0.02338 -0.1107 0.6993 0.0385
-9.000 -0.3247 0.02715 0.02105 -0.1102 0.6919 0.0383
-8.750 -0.3061 0.02548 0.01916 -0.1094 0.6849 0.0382
-8.500 -0.2857 0.02411 0.01757 -0.1086 0.6788 0.0382
-8.250 -0.2638 0.02290 0.01618 -0.1080 0.6728 0.0382
-8.000 -0.2411 0.02189 0.01498 -0.1074 0.6672 0.0382
-7.750 -0.2174 0.02105 0.01395 -0.1069 0.6620 0.0383
-7.500 -0.1927 0.02026 0.01306 -0.1065 0.6573 0.0384
-7.250 -0.1677 0.01947 0.01215 -0.1062 0.6524 0.0386
-7.000 -0.1428 0.01845 0.01103 -0.1059 0.6477 0.0388
-6.750 -0.1176 0.01770 0.01022 -0.1056 0.6431 0.0392
-6.500 -0.0917 0.01712 0.00965 -0.1054 0.6392 0.0397
-6.250 -0.0657 0.01664 0.00916 -0.1051 0.6348 0.0402
-6.000 -0.0398 0.01620 0.00866 -0.1048 0.6304 0.0406
-5.750 -0.0139 0.01581 0.00820 -0.1045 0.6262 0.0410
-5.500 0.0122 0.01544 0.00779 -0.1042 0.6224 0.0414
-5.250 0.0383 0.01505 0.00739 -0.1039 0.6185 0.0418
-5.000 0.0643 0.01471 0.00702 -0.1036 0.6143 0.0423
-4.750 0.0904 0.01442 0.00667 -0.1032 0.6102 0.0427
-4.500 0.1169 0.01422 0.00639 -0.1030 0.6061 0.0432
-4.250 0.1424 0.01384 0.00602 -0.1026 0.6025 0.0438
-4.000 0.1683 0.01353 0.00573 -0.1023 0.5985 0.0447
-3.750 0.1948 0.01330 0.00550 -0.1020 0.5942 0.0457
-3.500 0.2216 0.01315 0.00529 -0.1018 0.5901 0.0470
-3.250 0.2488 0.01306 0.00514 -0.1017 0.5859 0.0484
-3.000 0.2754 0.01283 0.00496 -0.1015 0.5822 0.0503
-2.750 0.3025 0.01269 0.00483 -0.1013 0.5778 0.0527
-2.500 0.3296 0.01256 0.00471 -0.1012 0.5734 0.0561
-2.250 0.3569 0.01251 0.00464 -0.1011 0.5689 0.0625
-2.000 0.3841 0.01241 0.00456 -0.1010 0.5649 0.0738
-1.750 0.4104 0.01219 0.00437 -0.1007 0.5604 0.0864
-1.500 0.4357 0.01187 0.00426 -0.1004 0.5557 0.1339
-1.250 0.4624 0.01181 0.00420 -0.1003 0.5509 0.1619
-1.000 0.4891 0.01172 0.00417 -0.1001 0.5462 0.1814
-0.750 0.5153 0.01155 0.00414 -0.1000 0.5413 0.2135
-0.500 0.5408 0.01133 0.00412 -0.0997 0.5363 0.2816
-0.250 0.5663 0.01121 0.00410 -0.0995 0.5313 0.3407
0.000 0.5912 0.01093 0.00410 -0.0991 0.5261 0.4162
0.250 0.6138 0.01055 0.00416 -0.0984 0.5204 0.5622
0.500 0.6384 0.01047 0.00420 -0.0978 0.5151 0.6250
0.750 0.6633 0.01039 0.00428 -0.0973 0.5098 0.6760
1.000 0.6879 0.01031 0.00436 -0.0967 0.5041 0.7263
1.250 0.7105 0.01023 0.00445 -0.0955 0.4985 0.7922
1.500 0.7330 0.01022 0.00460 -0.0943 0.4930 0.8537
1.750 0.7572 0.01026 0.00473 -0.0933 0.4869 0.8986
2.000 0.7850 0.01042 0.00486 -0.0932 0.4811 0.9345
2.250 0.8201 0.01061 0.00502 -0.0948 0.4754 0.9602
2.500 0.8583 0.01079 0.00517 -0.0971 0.4694 0.9764
2.750 0.9009 0.01105 0.00532 -0.1005 0.4633 0.9872
3.000 0.9451 0.01127 0.00549 -0.1042 0.4574 0.9945
3.250 0.9902 0.01148 0.00565 -0.1082 0.4512 1.0000
3.500 1.0039 0.01164 0.00574 -0.1057 0.4465 1.0000
3.750 1.0189 0.01181 0.00586 -0.1035 0.4422 1.0000
4.000 1.0355 0.01193 0.00598 -0.1015 0.4380 1.0000
4.250 1.0516 0.01209 0.00611 -0.0995 0.4337 1.0000
4.500 1.0675 0.01231 0.00626 -0.0974 0.4294 1.0000
4.750 1.0842 0.01253 0.00644 -0.0955 0.4252 1.0000
5.000 1.1021 0.01269 0.00661 -0.0939 0.4213 1.0000
5.250 1.1208 0.01291 0.00681 -0.0925 0.4171 1.0000
5.500 1.1399 0.01319 0.00703 -0.0912 0.4132 1.0000
5.750 1.1603 0.01352 0.00730 -0.0903 0.4092 1.0000
6.000 1.1810 0.01374 0.00756 -0.0894 0.4061 1.0000
6.250 1.2019 0.01400 0.00783 -0.0885 0.4025 1.0000
6.500 1.2223 0.01430 0.00811 -0.0877 0.3988 1.0000
6.750 1.2422 0.01467 0.00843 -0.0868 0.3951 1.0000
7.000 1.2632 0.01503 0.00876 -0.0861 0.3914 1.0000
7.250 1.2834 0.01534 0.00912 -0.0853 0.3883 1.0000
7.500 1.3038 0.01568 0.00947 -0.0846 0.3851 1.0000
7.750 1.3238 0.01605 0.00984 -0.0838 0.3819 1.0000
8.000 1.3434 0.01648 0.01024 -0.0830 0.3786 1.0000
8.250 1.3644 0.01692 0.01064 -0.0825 0.3751 1.0000
8.500 1.3832 0.01732 0.01110 -0.0817 0.3725 1.0000
8.750 1.4018 0.01776 0.01158 -0.0809 0.3693 1.0000
9.000 1.4205 0.01822 0.01206 -0.0801 0.3662 1.0000
9.250 1.4390 0.01872 0.01255 -0.0793 0.3633 1.0000
9.500 1.4582 0.01924 0.01304 -0.0787 0.3601 1.0000
9.750 1.4769 0.01976 0.01359 -0.0780 0.3573 1.0000
10.000 1.4927 0.02036 0.01426 -0.0770 0.3542 1.0000
10.250 1.5081 0.02100 0.01494 -0.0761 0.3505 1.0000
10.500 1.5231 0.02170 0.01564 -0.0751 0.3468 1.0000
10.750 1.5394 0.02238 0.01627 -0.0743 0.3428 1.0000
11.000 1.5537 0.02315 0.01712 -0.0734 0.3398 1.0000
11.250 1.5674 0.02397 0.01801 -0.0725 0.3364 1.0000
11.500 1.5805 0.02486 0.01894 -0.0715 0.3326 1.0000
11.750 1.5926 0.02581 0.01987 -0.0705 0.3286 1.0000
12.000 1.6047 0.02680 0.02087 -0.0696 0.3246 1.0000
12.250 1.6159 0.02791 0.02207 -0.0688 0.3209 1.0000
12.500 1.6270 0.02905 0.02327 -0.0679 0.3170 1.0000
12.750 1.6370 0.03029 0.02450 -0.0671 0.3132 1.0000
13.000 1.6478 0.03146 0.02567 -0.0662 0.3094 1.0000
13.250 1.6578 0.03283 0.02715 -0.0656 0.3060 1.0000
13.500 1.6674 0.03422 0.02861 -0.0649 0.3021 1.0000
13.750 1.6753 0.03576 0.03016 -0.0642 0.2982 1.0000
14.000 1.6828 0.03728 0.03166 -0.0633 0.2943 1.0000
14.250 1.6914 0.03889 0.03339 -0.0629 0.2909 1.0000
14.500 1.6982 0.04067 0.03524 -0.0623 0.2866 1.0000
14.750 1.7023 0.04265 0.03724 -0.0616 0.2821 1.0000
15.000 1.7063 0.04464 0.03925 -0.0609 0.2778 1.0000
15.250 1.7115 0.04668 0.04139 -0.0605 0.2733 1.0000
15.500 1.7140 0.04892 0.04367 -0.0600 0.2684 1.0000
15.750 1.7133 0.05142 0.04616 -0.0592 0.2636 1.0000
16.000 1.7174 0.05363 0.04848 -0.0589 0.2592 1.0000
16.250 1.7178 0.05617 0.05107 -0.0585 0.2538 1.0000
16.500 1.7131 0.05921 0.05411 -0.0579 0.2484 1.0000
16.750 1.7134 0.06185 0.05685 -0.0576 0.2427 1.0000
17.000 1.7077 0.06509 0.06010 -0.0571 0.2364 1.0000
17.250 1.7028 0.06831 0.06338 -0.0568 0.2303 1.0000
17.500 1.6947 0.07194 0.06704 -0.0565 0.2231 1.0000
17.750 1.6868 0.07555 0.07069 -0.0562 0.2161 1.0000
18.000 1.6732 0.07986 0.07503 -0.0560 0.2080 1.0000
18.250 1.6614 0.08405 0.07926 -0.0559 0.1999 1.0000
18.500 1.6427 0.08912 0.08432 -0.0558 0.1914 1.0000
18.750 1.6268 0.09390 0.08913 -0.0559 0.1820 1.0000
19.000 1.6094 0.09892 0.09416 -0.0562 0.1731 1.0000
19.250 1.5886 0.10447 0.09971 -0.0566 0.1647 1.0000
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