GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 421 AIRFOIL (goe421-il) Reynolds number: 200,000 Max Cl/Cd: 68.19 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe421-il-200000.txt Download as CSV file: xf-goe421-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 421 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0030 0.05932 0.05519 -0.1728 0.8793 0.0747
-9.750 -0.1408 0.04033 0.03538 -0.1858 0.8601 0.0718
-9.500 -0.1609 0.03846 0.03322 -0.1813 0.8486 0.0722
-9.250 -0.1454 0.03505 0.02923 -0.1832 0.8455 0.0735
-9.000 -0.1179 0.03225 0.02610 -0.1856 0.8438 0.0751
-8.750 -0.1173 0.03186 0.02571 -0.1814 0.8344 0.0761
-8.500 -0.0884 0.03067 0.02442 -0.1824 0.8314 0.0781
-8.250 -0.0558 0.02915 0.02267 -0.1842 0.8294 0.0803
-8.000 -0.0212 0.02764 0.02079 -0.1862 0.8277 0.0825
-7.750 0.0146 0.02601 0.01900 -0.1885 0.8263 0.0851
-7.500 0.0125 0.02607 0.01909 -0.1834 0.8161 0.0864
-7.250 0.0472 0.02510 0.01801 -0.1849 0.8136 0.0895
-7.000 0.0844 0.02409 0.01677 -0.1869 0.8116 0.0926
-6.750 0.1217 0.02289 0.01549 -0.1891 0.8099 0.0963
-6.500 0.1271 0.02298 0.01563 -0.1852 0.8018 0.0987
-6.250 0.1566 0.02240 0.01494 -0.1857 0.7981 0.1030
-6.000 0.1921 0.02147 0.01396 -0.1873 0.7956 0.1078
-5.750 0.2302 0.02076 0.01320 -0.1894 0.7935 0.1146
-5.500 0.2546 0.02038 0.01283 -0.1890 0.7892 0.1210
-5.250 0.2683 0.02041 0.01286 -0.1866 0.7825 0.1275
-5.000 0.3017 0.01995 0.01243 -0.1877 0.7794 0.1392
-4.750 0.3395 0.01963 0.01211 -0.1896 0.7770 0.1563
-4.500 0.3802 0.01957 0.01200 -0.1919 0.7749 0.1765
-4.250 0.3836 0.02026 0.01270 -0.1874 0.7669 0.1879
-4.000 0.4139 0.02035 0.01276 -0.1879 0.7631 0.2031
-3.750 0.4499 0.02023 0.01261 -0.1894 0.7604 0.2171
-3.500 0.4898 0.02001 0.01228 -0.1917 0.7581 0.2303
-3.250 0.4978 0.02046 0.01278 -0.1882 0.7509 0.2376
-3.000 0.5269 0.02028 0.01251 -0.1884 0.7461 0.2470
-2.750 0.5659 0.01993 0.01211 -0.1904 0.7427 0.2569
-2.500 0.6012 0.01967 0.01172 -0.1918 0.7386 0.2655
-2.250 0.6130 0.01982 0.01196 -0.1888 0.7311 0.2712
-2.000 0.6483 0.01956 0.01156 -0.1901 0.7265 0.2800
-1.750 0.6905 0.01910 0.01103 -0.1928 0.7231 0.2880
-1.500 0.6995 0.01935 0.01134 -0.1894 0.7158 0.2926
-1.250 0.7278 0.01926 0.01117 -0.1895 0.7110 0.2989
-1.000 0.7645 0.01897 0.01083 -0.1912 0.7076 0.3059
-0.750 0.7917 0.01897 0.01083 -0.1912 0.7032 0.3122
-0.500 0.8071 0.01912 0.01098 -0.1889 0.6971 0.3161
-0.250 0.8379 0.01899 0.01075 -0.1895 0.6928 0.3201
0.000 0.8753 0.01870 0.01044 -0.1914 0.6895 0.3256
0.250 0.8932 0.01886 0.01065 -0.1897 0.6841 0.3306
0.500 0.9133 0.01893 0.01072 -0.1884 0.6784 0.3360
0.750 0.9467 0.01872 0.01048 -0.1895 0.6742 0.3426
1.000 0.9840 0.01854 0.01026 -0.1913 0.6703 0.3514
1.250 0.9912 0.01883 0.01062 -0.1876 0.6632 0.3587
1.500 1.0200 0.01867 0.01051 -0.1878 0.6580 0.3703
1.750 1.0588 0.01842 0.01024 -0.1900 0.6539 0.3901
2.000 1.0662 0.01865 0.01063 -0.1863 0.6468 0.4083
2.250 1.0919 0.01851 0.01061 -0.1860 0.6411 0.4420
2.500 1.1289 0.01816 0.01040 -0.1879 0.6367 0.5010
2.750 1.1349 0.01824 0.01084 -0.1840 0.6294 0.5744
3.000 1.1555 0.01755 0.01083 -0.1821 0.6234 1.0000
3.250 1.1915 0.01753 0.01063 -0.1837 0.6182 1.0000
3.500 1.1919 0.01791 0.01105 -0.1787 0.6101 1.0000
3.750 1.2200 0.01793 0.01094 -0.1788 0.6038 1.0000
4.000 1.2327 0.01824 0.01123 -0.1762 0.5962 1.0000
4.250 1.2501 0.01843 0.01136 -0.1744 0.5884 1.0000
4.500 1.2703 0.01863 0.01149 -0.1732 0.5808 1.0000
4.750 1.2811 0.01897 0.01181 -0.1703 0.5717 1.0000
5.000 1.2991 0.01922 0.01200 -0.1687 0.5630 1.0000
5.250 1.3117 0.01957 0.01231 -0.1663 0.5532 1.0000
5.500 1.3226 0.02004 0.01275 -0.1636 0.5428 1.0000
5.750 1.3436 0.02026 0.01285 -0.1626 0.5333 1.0000
6.000 1.3477 0.02099 0.01360 -0.1590 0.5214 1.0000
6.250 1.3623 0.02148 0.01401 -0.1571 0.5109 1.0000
6.500 1.3770 0.02199 0.01443 -0.1553 0.5005 1.0000
6.750 1.3864 0.02276 0.01518 -0.1528 0.4894 1.0000
7.000 1.4055 0.02322 0.01551 -0.1517 0.4805 1.0000
7.250 1.4149 0.02406 0.01635 -0.1493 0.4707 1.0000
7.500 1.4353 0.02455 0.01672 -0.1486 0.4632 1.0000
7.750 1.4459 0.02542 0.01761 -0.1465 0.4550 1.0000
8.000 1.4694 0.02582 0.01788 -0.1462 0.4489 1.0000
8.250 1.4814 0.02668 0.01878 -0.1444 0.4422 1.0000
8.500 1.4966 0.02741 0.01949 -0.1430 0.4360 1.0000
8.750 1.5235 0.02772 0.01966 -0.1433 0.4306 1.0000
9.000 1.5304 0.02879 0.02083 -0.1409 0.4250 1.0000
9.250 1.5450 0.02956 0.02162 -0.1396 0.4197 1.0000
9.500 1.5705 0.02992 0.02188 -0.1397 0.4154 1.0000
9.750 1.5865 0.03070 0.02269 -0.1386 0.4112 1.0000
10.000 1.5977 0.03167 0.02374 -0.1369 0.4071 1.0000
10.250 1.6148 0.03239 0.02450 -0.1361 0.4035 1.0000
10.500 1.6365 0.03292 0.02500 -0.1358 0.4002 1.0000
10.750 1.6688 0.03307 0.02506 -0.1368 0.3967 1.0000
11.000 1.6717 0.03440 0.02655 -0.1342 0.3933 1.0000
11.250 1.6817 0.03546 0.02772 -0.1325 0.3899 1.0000
11.500 1.6966 0.03630 0.02860 -0.1315 0.3866 1.0000
11.750 1.7161 0.03688 0.02918 -0.1310 0.3831 1.0000
12.000 1.7414 0.03726 0.02951 -0.1312 0.3791 1.0000
12.250 1.7379 0.03900 0.03142 -0.1281 0.3754 1.0000
12.500 1.7422 0.04037 0.03289 -0.1260 0.3712 1.0000
12.750 1.7550 0.04124 0.03376 -0.1249 0.3668 1.0000
13.000 1.7800 0.04151 0.03397 -0.1250 0.3623 1.0000
13.250 1.7713 0.04375 0.03641 -0.1218 0.3586 1.0000
13.500 1.7713 0.04552 0.03829 -0.1196 0.3541 1.0000
13.750 1.7824 0.04655 0.03933 -0.1185 0.3497 1.0000
14.000 1.8056 0.04683 0.03956 -0.1184 0.3454 1.0000
14.250 1.7959 0.04945 0.04240 -0.1156 0.3420 1.0000
14.500 1.7933 0.05163 0.04472 -0.1136 0.3378 1.0000
14.750 1.7996 0.05309 0.04621 -0.1123 0.3330 1.0000
15.000 1.8139 0.05392 0.04701 -0.1115 0.3280 1.0000
15.250 1.7981 0.05742 0.05073 -0.1090 0.3234 1.0000
15.500 1.7952 0.05986 0.05328 -0.1074 0.3183 1.0000
15.750 1.8131 0.06030 0.05363 -0.1069 0.3129 1.0000
16.000 1.7978 0.06413 0.05769 -0.1049 0.3086 1.0000
16.250 1.7879 0.06755 0.06127 -0.1034 0.3035 1.0000
16.500 1.7940 0.06925 0.06296 -0.1026 0.2976 1.0000
16.750 1.7820 0.07306 0.06694 -0.1013 0.2920 1.0000
17.000 1.7675 0.07728 0.07134 -0.1001 0.2857 1.0000
17.250 1.7707 0.07944 0.07346 -0.0994 0.2789 1.0000
17.500 1.7472 0.08505 0.07933 -0.0985 0.2721 1.0000
17.750 1.7440 0.08811 0.08240 -0.0980 0.2641 1.0000
18.000 1.7188 0.09422 0.08875 -0.0974 0.2557 1.0000
18.250 1.7049 0.09886 0.09347 -0.0972 0.2461 1.0000
18.500 1.6851 0.10440 0.09910 -0.0971 0.2345 1.0000
18.750 1.6618 0.11055 0.10533 -0.0973 0.2203 1.0000
19.000 1.6402 0.11648 0.11126 -0.0978 0.2031 1.0000
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