GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 200,000 Max Cl/Cd: 67.33 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe654-il-200000.txt Download as CSV file: xf-goe654-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1533 0.12409 0.12085 -0.0397 1.0000 0.0509
-11.750 -0.1661 0.12201 0.11881 -0.0415 1.0000 0.0525
-11.500 -0.1862 0.11974 0.11659 -0.0441 1.0000 0.0529
-11.250 -0.1771 0.11614 0.11305 -0.0420 1.0000 0.0534
-11.000 -0.1703 0.11426 0.11123 -0.0393 1.0000 0.0540
-10.750 -0.1653 0.11233 0.10936 -0.0381 0.9988 0.0549
-10.500 -0.1474 0.10821 0.10522 -0.0415 0.9951 0.0565
-10.250 -0.1358 0.10391 0.10092 -0.0455 0.9902 0.0595
-10.000 -0.1565 0.09874 0.09576 -0.0557 0.9841 0.0617
-9.750 -0.1303 0.09340 0.09042 -0.0560 0.9781 0.0626
-9.500 -0.1029 0.08961 0.08663 -0.0575 0.9715 0.0640
-9.250 -0.0849 0.08573 0.08274 -0.0602 0.9619 0.0659
-9.000 -0.0706 0.08112 0.07811 -0.0648 0.9540 0.0689
-8.750 -0.0935 0.07398 0.07097 -0.0798 0.9416 0.0720
-8.500 -0.0601 0.06925 0.06622 -0.0781 0.9314 0.0733
-8.250 -0.0256 0.06608 0.06299 -0.0796 0.9179 0.0758
-8.000 -0.1435 0.07337 0.07026 -0.0822 0.9382 0.0730
-7.750 -0.1063 0.07144 0.06830 -0.0811 0.9301 0.0747
-7.500 -0.0755 0.06781 0.06461 -0.0869 0.9148 0.0781
-7.250 -0.0929 0.05702 0.05340 -0.1077 0.8813 0.0846
-7.000 -0.0647 0.05515 0.05160 -0.1064 0.8646 0.0859
-6.750 -0.0462 0.05348 0.04985 -0.1057 0.8456 0.0877
-6.500 -0.0351 0.05110 0.04732 -0.1062 0.8266 0.0905
-6.250 -0.0454 0.04592 0.04156 -0.1095 0.8081 0.0985
-6.000 -0.0269 0.04394 0.03960 -0.1084 0.7916 0.1000
-5.750 -0.0102 0.04234 0.03792 -0.1075 0.7754 0.1026
-5.500 -0.0042 0.03971 0.03472 -0.1076 0.7601 0.1131
-5.250 0.0150 0.03757 0.03261 -0.1069 0.7457 0.1151
-5.000 0.0342 0.03617 0.03114 -0.1060 0.7317 0.1192
-4.750 0.0496 0.03422 0.02884 -0.1054 0.7192 0.1304
-4.500 0.0658 0.02565 0.01887 -0.1032 0.7103 0.0753
-4.250 0.0882 0.02306 0.01572 -0.1017 0.6991 0.0662
-4.000 0.1133 0.02173 0.01369 -0.1002 0.6893 0.0621
-3.750 0.1381 0.02090 0.01268 -0.0994 0.6785 0.0617
-3.500 0.1636 0.01977 0.01133 -0.0988 0.6704 0.0621
-3.250 0.1887 0.01869 0.01017 -0.0981 0.6613 0.0630
-3.000 0.2153 0.01798 0.00931 -0.0976 0.6542 0.0632
-2.750 0.2409 0.01733 0.00861 -0.0970 0.6459 0.0636
-2.500 0.2674 0.01678 0.00797 -0.0964 0.6392 0.0643
-2.250 0.2925 0.01632 0.00752 -0.0957 0.6313 0.0655
-2.000 0.3183 0.01594 0.00708 -0.0951 0.6244 0.0670
-1.750 0.3437 0.01563 0.00675 -0.0944 0.6176 0.0689
-1.500 0.3695 0.01543 0.00649 -0.0938 0.6107 0.0720
-1.250 0.3948 0.01509 0.00613 -0.0932 0.6047 0.0766
-1.000 0.4199 0.01489 0.00593 -0.0925 0.5972 0.0823
-0.750 0.4458 0.01465 0.00565 -0.0919 0.5907 0.0958
-0.500 0.4636 0.01340 0.00559 -0.0905 0.5842 0.4051
-0.250 0.4816 0.01280 0.00568 -0.0884 0.5777 0.6107
0.000 0.5648 0.01214 0.00575 -0.0984 0.5687 0.9775
0.250 0.6103 0.01225 0.00569 -0.1020 0.5602 1.0000
0.500 0.6337 0.01243 0.00569 -0.1011 0.5535 1.0000
0.750 0.6559 0.01255 0.00573 -0.0999 0.5454 1.0000
1.000 0.6806 0.01276 0.00573 -0.0992 0.5387 1.0000
1.250 0.7022 0.01289 0.00584 -0.0980 0.5304 1.0000
1.500 0.7265 0.01308 0.00586 -0.0972 0.5234 1.0000
1.750 0.7486 0.01325 0.00600 -0.0960 0.5150 1.0000
2.000 0.7725 0.01342 0.00604 -0.0951 0.5072 1.0000
2.250 0.7947 0.01360 0.00617 -0.0940 0.4983 1.0000
2.500 0.8183 0.01377 0.00622 -0.0931 0.4902 1.0000
2.750 0.8405 0.01395 0.00637 -0.0919 0.4813 1.0000
3.000 0.8643 0.01413 0.00643 -0.0911 0.4734 1.0000
3.250 0.8865 0.01432 0.00661 -0.0900 0.4646 1.0000
3.500 0.9102 0.01450 0.00669 -0.0891 0.4570 1.0000
3.750 0.9325 0.01470 0.00687 -0.0880 0.4483 1.0000
4.000 0.9560 0.01488 0.00696 -0.0872 0.4410 1.0000
4.250 0.9787 0.01511 0.00718 -0.0862 0.4333 1.0000
4.500 1.0020 0.01532 0.00734 -0.0854 0.4264 1.0000
4.750 1.0253 0.01559 0.00755 -0.0846 0.4198 1.0000
5.000 1.0480 0.01582 0.00776 -0.0837 0.4128 1.0000
5.250 1.0727 0.01611 0.00793 -0.0831 0.4073 1.0000
5.500 1.0945 0.01638 0.00827 -0.0821 0.4009 1.0000
5.750 1.1177 0.01665 0.00849 -0.0813 0.3952 1.0000
6.000 1.1416 0.01700 0.00879 -0.0807 0.3900 1.0000
6.250 1.1635 0.01731 0.00914 -0.0798 0.3842 1.0000
6.500 1.1871 0.01763 0.00941 -0.0791 0.3792 1.0000
6.750 1.2106 0.01802 0.00978 -0.0785 0.3742 1.0000
7.000 1.2318 0.01837 0.01018 -0.0775 0.3688 1.0000
7.250 1.2548 0.01871 0.01048 -0.0768 0.3638 1.0000
7.500 1.2782 0.01916 0.01090 -0.0763 0.3589 1.0000
7.750 1.2976 0.01952 0.01135 -0.0750 0.3536 1.0000
8.000 1.3198 0.01989 0.01170 -0.0742 0.3486 1.0000
8.250 1.3440 0.02039 0.01215 -0.0738 0.3440 1.0000
8.500 1.3617 0.02080 0.01269 -0.0723 0.3393 1.0000
8.750 1.3826 0.02122 0.01314 -0.0714 0.3348 1.0000
9.000 1.4076 0.02172 0.01357 -0.0712 0.3305 1.0000
9.250 1.4230 0.02218 0.01416 -0.0694 0.3254 1.0000
9.500 1.4383 0.02253 0.01457 -0.0675 0.3195 1.0000
9.750 1.4613 0.02300 0.01491 -0.0671 0.3133 1.0000
10.000 1.4680 0.02339 0.01549 -0.0638 0.3079 1.0000
10.250 1.4803 0.02376 0.01590 -0.0615 0.3026 1.0000
10.500 1.5006 0.02427 0.01634 -0.0607 0.2973 1.0000
10.750 1.5019 0.02474 0.01700 -0.0566 0.2925 1.0000
11.000 1.5099 0.02521 0.01753 -0.0539 0.2871 1.0000
11.250 1.5262 0.02573 0.01797 -0.0526 0.2819 1.0000
11.500 1.5274 0.02643 0.01889 -0.0492 0.2771 1.0000
11.750 1.5333 0.02710 0.01965 -0.0467 0.2720 1.0000
12.000 1.5468 0.02771 0.02020 -0.0452 0.2670 1.0000
12.250 1.5447 0.02876 0.02147 -0.0422 0.2615 1.0000
12.500 1.5473 0.02976 0.02254 -0.0400 0.2557 1.0000
12.750 1.5532 0.03079 0.02359 -0.0382 0.2504 1.0000
13.000 1.5523 0.03223 0.02523 -0.0362 0.2441 1.0000
13.250 1.5559 0.03356 0.02657 -0.0347 0.2388 1.0000
13.500 1.5572 0.03520 0.02835 -0.0334 0.2330 1.0000
13.750 1.5568 0.03704 0.03028 -0.0321 0.2265 1.0000
14.000 1.5545 0.03915 0.03246 -0.0311 0.2193 1.0000
14.250 1.5514 0.04151 0.03491 -0.0302 0.2119 1.0000
14.500 1.5474 0.04411 0.03759 -0.0296 0.2044 1.0000
14.750 1.5412 0.04707 0.04060 -0.0292 0.1966 1.0000
15.000 1.5366 0.05007 0.04370 -0.0290 0.1891 1.0000
15.500 1.5193 0.05733 0.05106 -0.0292 0.1728 1.0000
15.750 1.5101 0.06122 0.05499 -0.0296 0.1663 1.0000
16.000 1.4997 0.06538 0.05923 -0.0301 0.1583 1.0000
16.250 1.4861 0.07010 0.06399 -0.0309 0.1496 1.0000
16.500 1.4711 0.07509 0.06902 -0.0319 0.1426 1.0000
16.750 1.4594 0.07980 0.07382 -0.0329 0.1349 1.0000
17.000 1.4411 0.08556 0.07962 -0.0343 0.1265 1.0000
17.250 1.4251 0.09116 0.08527 -0.0359 0.1192 1.0000
17.500 1.4077 0.09711 0.09128 -0.0377 0.1105 1.0000
17.750 1.3897 0.10330 0.09753 -0.0397 0.1017 1.0000
18.000 1.3705 0.10982 0.10409 -0.0420 0.0903 1.0000
18.250 1.3443 0.11759 0.11181 -0.0450 0.0725 1.0000
18.500 1.3186 0.12541 0.11959 -0.0483 0.0587 1.0000
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