GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 572 AIRFOIL (goe572-il) Reynolds number: 200,000 Max Cl/Cd: 55.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe572-il-200000.txt Download as CSV file: xf-goe572-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 572 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
------ -------- --------- --------- -------- -------- --------
-11.250 0.2434 0.09823 0.09331 -0.1403 0.6888 0.0466
-11.000 0.2392 0.09636 0.09141 -0.1426 0.6787 0.0469
-10.750 0.2446 0.09279 0.08775 -0.1434 0.6698 0.0474
-10.500 0.2616 0.09003 0.08492 -0.1424 0.6583 0.0480
-10.250 0.2734 0.08773 0.08254 -0.1424 0.6489 0.0487
-10.000 0.2832 0.08569 0.08045 -0.1423 0.6403 0.0506
-9.750 0.2883 0.08350 0.07820 -0.1430 0.6334 0.0524
-9.500 0.2831 0.08147 0.07620 -0.1446 0.6273 0.0548
-9.250 0.2644 0.07944 0.07422 -0.1480 0.6233 0.0556
-9.000 0.2788 0.07571 0.07042 -0.1464 0.6169 0.0569
-8.750 0.2874 0.07362 0.06832 -0.1457 0.6100 0.0575
-8.500 0.2958 0.07164 0.06627 -0.1453 0.6042 0.0586
-8.250 0.2993 0.06962 0.06426 -0.1450 0.5986 0.0603
-8.000 0.2963 0.06737 0.06204 -0.1451 0.5933 0.0626
-7.750 0.2835 0.06485 0.05954 -0.1462 0.5896 0.0643
-7.500 0.2448 0.06273 0.05739 -0.1455 0.5873 0.0657
-7.250 0.2195 0.06073 0.05523 -0.1434 0.5844 0.0662
-7.000 0.2246 0.05666 0.05125 -0.1421 0.5791 0.0671
-6.750 0.2438 0.05513 0.04976 -0.1404 0.5735 0.0687
-6.500 0.2538 0.05376 0.04830 -0.1389 0.5688 0.0710
-6.250 0.2531 0.05184 0.04638 -0.1368 0.5642 0.0736
-6.000 0.2284 0.05130 0.04527 -0.1321 0.5617 0.0786
-5.750 0.2378 0.04636 0.04048 -0.1315 0.5571 0.0803
-5.500 0.2537 0.04472 0.03879 -0.1305 0.5529 0.0820
-5.250 0.2617 0.04330 0.03738 -0.1279 0.5481 0.0847
-5.000 0.2586 0.04436 0.03778 -0.1223 0.5443 0.0927
-4.750 0.2672 0.03937 0.03295 -0.1214 0.5403 0.0952
-4.500 0.2854 0.03802 0.03152 -0.1205 0.5362 0.0983
-4.250 0.2853 0.03723 0.03039 -0.1155 0.5322 0.1096
-4.000 0.2999 0.03522 0.02848 -0.1139 0.5272 0.1123
-3.750 0.3154 0.03404 0.02718 -0.1120 0.5231 0.1174
-3.500 0.3180 0.02828 0.02030 -0.1048 0.5212 0.0743
-3.250 0.3323 0.02641 0.01807 -0.1018 0.5176 0.0714
-3.000 0.3465 0.02467 0.01583 -0.0983 0.5131 0.0685
-2.750 0.3680 0.02382 0.01484 -0.0970 0.5087 0.0697
-2.500 0.3933 0.02321 0.01404 -0.0964 0.5046 0.0718
-2.250 0.4147 0.02259 0.01327 -0.0949 0.5002 0.0731
-2.000 0.4363 0.02199 0.01255 -0.0935 0.4954 0.0744
-1.750 0.4617 0.02154 0.01193 -0.0928 0.4913 0.0765
-1.500 0.4910 0.02115 0.01133 -0.0930 0.4876 0.0792
-1.250 0.5125 0.02055 0.01080 -0.0918 0.4831 0.0819
-1.000 0.5337 0.02023 0.01050 -0.0904 0.4783 0.0852
-0.750 0.5583 0.02001 0.01019 -0.0897 0.4744 0.0905
-0.500 0.5867 0.01970 0.00979 -0.0899 0.4707 0.0970
-0.250 0.6004 0.01955 0.00976 -0.0871 0.4663 0.1038
0.000 0.6181 0.01931 0.00956 -0.0851 0.4620 0.1163
0.250 0.6394 0.01901 0.00935 -0.0838 0.4583 0.1520
0.500 0.9215 0.01803 0.01013 -0.1381 0.4453 1.0000
0.750 0.9421 0.01816 0.01012 -0.1369 0.4417 1.0000
1.000 0.9654 0.01840 0.01016 -0.1362 0.4382 1.0000
1.250 0.9787 0.01860 0.01040 -0.1336 0.4341 1.0000
1.500 0.9960 0.01879 0.01053 -0.1317 0.4300 1.0000
1.750 1.0163 0.01895 0.01058 -0.1304 0.4265 1.0000
2.000 1.0403 0.01918 0.01064 -0.1300 0.4233 1.0000
2.250 1.0545 0.01947 0.01096 -0.1275 0.4196 1.0000
2.500 1.0698 0.01971 0.01118 -0.1253 0.4156 1.0000
2.750 1.0885 0.01989 0.01130 -0.1238 0.4119 1.0000
3.000 1.1104 0.02011 0.01139 -0.1229 0.4089 1.0000
3.250 1.1300 0.02046 0.01167 -0.1217 0.4057 1.0000
3.500 1.1425 0.02078 0.01205 -0.1190 0.4022 1.0000
3.750 1.1583 0.02104 0.01230 -0.1170 0.3985 1.0000
4.000 1.1776 0.02128 0.01246 -0.1156 0.3954 1.0000
4.250 1.2017 0.02156 0.01260 -0.1153 0.3924 1.0000
4.500 1.2140 0.02195 0.01304 -0.1127 0.3892 1.0000
4.750 1.2249 0.02231 0.01345 -0.1098 0.3858 1.0000
5.000 1.2396 0.02261 0.01373 -0.1077 0.3825 1.0000
5.250 1.2583 0.02287 0.01393 -0.1063 0.3795 1.0000
5.500 1.2844 0.02322 0.01416 -0.1065 0.3767 1.0000
5.750 1.2920 0.02369 0.01470 -0.1031 0.3740 1.0000
6.000 1.2957 0.02409 0.01518 -0.0990 0.3711 1.0000
6.250 1.3052 0.02445 0.01556 -0.0960 0.3681 1.0000
6.500 1.3206 0.02478 0.01588 -0.0942 0.3655 1.0000
6.750 1.3416 0.02511 0.01613 -0.0935 0.3630 1.0000
7.000 1.3650 0.02563 0.01659 -0.0934 0.3603 1.0000
7.250 1.3616 0.02622 0.01733 -0.0884 0.3576 1.0000
7.500 1.3676 0.02681 0.01801 -0.0852 0.3549 1.0000
7.750 1.3786 0.02732 0.01854 -0.0830 0.3522 1.0000
8.000 1.3954 0.02775 0.01896 -0.0817 0.3498 1.0000
8.250 1.4187 0.02813 0.01927 -0.0816 0.3474 1.0000
8.500 1.4402 0.02876 0.01989 -0.0813 0.3451 1.0000
8.750 1.4325 0.02976 0.02106 -0.0765 0.3427 1.0000
9.000 1.4330 0.03073 0.02214 -0.0732 0.3400 1.0000
9.250 1.4403 0.03151 0.02298 -0.0709 0.3375 1.0000
9.500 1.4545 0.03215 0.02364 -0.0697 0.3353 1.0000
9.750 1.4760 0.03253 0.02398 -0.0695 0.3331 1.0000
10.000 1.4962 0.03302 0.02443 -0.0691 0.3300 1.0000
10.250 1.4804 0.03481 0.02642 -0.0645 0.3276 1.0000
10.500 1.4718 0.03643 0.02817 -0.0612 0.3245 1.0000
10.750 1.4771 0.03741 0.02921 -0.0595 0.3215 1.0000
11.000 1.4988 0.03738 0.02907 -0.0592 0.3180 1.0000
11.250 1.5141 0.03809 0.02977 -0.0586 0.3151 1.0000
11.500 1.4934 0.04089 0.03279 -0.0551 0.3127 1.0000
11.750 1.4802 0.04352 0.03559 -0.0527 0.3100 1.0000
12.000 1.4805 0.04517 0.03729 -0.0514 0.3068 1.0000
12.250 1.4984 0.04550 0.03759 -0.0511 0.3039 1.0000
12.500 1.5114 0.04623 0.03828 -0.0505 0.3001 1.0000
12.750 1.4883 0.05024 0.04252 -0.0484 0.2982 1.0000
13.000 1.4610 0.05490 0.04738 -0.0467 0.2957 1.0000
13.250 1.4508 0.05809 0.05067 -0.0458 0.2924 1.0000
13.500 1.5032 0.05472 0.04704 -0.0465 0.2870 1.0000
13.750 1.4807 0.05933 0.05186 -0.0454 0.2851 1.0000
14.000 1.4374 0.06653 0.05933 -0.0442 0.2834 1.0000
14.750 1.4427 0.07319 0.06609 -0.0439 0.2712 1.0000
15.000 1.3788 0.08393 0.07714 -0.0435 0.2708 1.0000
15.250 0.7799 0.19123 0.18518 -0.0653 0.2912 1.0000
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Polar data table (+)
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