GOE 390 AIRFOIL (goe390-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 390 AIRFOIL (goe390-il) Reynolds number: 200,000 Max Cl/Cd: 62.94 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe390-il-200000.txt Download as CSV file: xf-goe390-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 390 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 0.0936 0.11092 0.10681 -0.1055 0.8698 0.0803
-11.000 0.0983 0.10833 0.10417 -0.1062 0.8617 0.0822
-10.750 0.0765 0.10395 0.09976 -0.1111 0.8539 0.0847
-10.500 0.0955 0.10184 0.09761 -0.1098 0.8454 0.0852
-10.250 0.1104 0.09989 0.09558 -0.1090 0.8380 0.0862
-10.000 0.1209 0.09777 0.09345 -0.1093 0.8286 0.0880
-9.750 0.0926 0.09267 0.08833 -0.1158 0.8215 0.0924
-9.500 0.1135 0.09092 0.08653 -0.1139 0.8132 0.0930
-9.250 0.1293 0.08909 0.08466 -0.1131 0.8044 0.0940
-9.000 -0.0691 0.04803 0.04315 -0.1490 0.8015 0.0701
-8.750 -0.0779 0.04370 0.03857 -0.1500 0.7946 0.0697
-8.500 -0.0944 0.03849 0.03288 -0.1500 0.7862 0.0694
-8.250 -0.0981 0.03443 0.02813 -0.1492 0.7798 0.0699
-8.000 -0.0885 0.03202 0.02529 -0.1482 0.7734 0.0708
-7.750 -0.0664 0.03114 0.02450 -0.1476 0.7662 0.0718
-7.500 -0.0448 0.02998 0.02320 -0.1471 0.7608 0.0728
-7.250 -0.0236 0.02852 0.02144 -0.1467 0.7563 0.0741
-7.000 -0.0064 0.02723 0.01988 -0.1455 0.7502 0.0755
-6.750 0.0126 0.02609 0.01828 -0.1444 0.7444 0.0770
-6.500 0.0380 0.02494 0.01714 -0.1443 0.7395 0.0788
-6.250 0.0657 0.02428 0.01639 -0.1443 0.7353 0.0812
-6.000 0.0864 0.02366 0.01555 -0.1432 0.7292 0.0839
-5.750 0.1106 0.02282 0.01473 -0.1427 0.7237 0.0863
-5.500 0.1376 0.02222 0.01405 -0.1425 0.7190 0.0894
-5.250 0.1658 0.02148 0.01309 -0.1424 0.7149 0.0929
-5.000 0.1885 0.02111 0.01285 -0.1416 0.7089 0.0962
-4.750 0.2138 0.02073 0.01232 -0.1410 0.7030 0.1006
-4.500 0.2417 0.02027 0.01193 -0.1410 0.6982 0.1047
-4.250 0.2717 0.01997 0.01142 -0.1412 0.6941 0.1097
-4.000 0.2937 0.01977 0.01140 -0.1402 0.6879 0.1137
-3.750 0.3201 0.01959 0.01112 -0.1398 0.6821 0.1190
-3.500 0.3490 0.01931 0.01084 -0.1398 0.6772 0.1240
-3.250 0.3771 0.01921 0.01062 -0.1397 0.6720 0.1301
-3.000 0.4003 0.01904 0.01054 -0.1388 0.6652 0.1352
-2.750 0.4283 0.01889 0.01029 -0.1386 0.6595 0.1422
-2.500 0.4582 0.01859 0.00998 -0.1389 0.6548 0.1492
-2.250 0.4815 0.01847 0.00987 -0.1380 0.6483 0.1574
-2.000 0.5069 0.01822 0.00967 -0.1375 0.6418 0.1674
-1.750 0.5356 0.01787 0.00931 -0.1375 0.6363 0.1820
-1.500 0.5605 0.01768 0.00918 -0.1369 0.6299 0.1995
-1.250 0.5844 0.01751 0.00909 -0.1362 0.6227 0.2165
-1.000 0.6129 0.01735 0.00890 -0.1362 0.6168 0.2332
-0.750 0.6390 0.01733 0.00888 -0.1359 0.6105 0.2485
-0.500 0.6627 0.01731 0.00889 -0.1351 0.6031 0.2638
-0.250 0.6906 0.01716 0.00875 -0.1350 0.5969 0.2823
0.000 0.7158 0.01711 0.00877 -0.1345 0.5902 0.3068
0.250 0.7382 0.01695 0.00880 -0.1336 0.5826 0.3452
0.500 0.7641 0.01661 0.00876 -0.1333 0.5767 0.4364
0.750 0.7852 0.01638 0.00896 -0.1320 0.5702 0.5740
1.000 0.8024 0.01606 0.00914 -0.1297 0.5632 0.7071
1.250 0.8600 0.01578 0.00918 -0.1345 0.5566 0.9737
1.500 0.8936 0.01600 0.00931 -0.1359 0.5495 1.0000
1.750 0.9138 0.01617 0.00937 -0.1345 0.5429 1.0000
2.000 0.9397 0.01631 0.00934 -0.1342 0.5376 1.0000
2.250 0.9608 0.01655 0.00951 -0.1330 0.5316 1.0000
2.500 0.9806 0.01676 0.00966 -0.1316 0.5252 1.0000
2.750 1.0055 0.01692 0.00969 -0.1311 0.5198 1.0000
3.000 1.0313 0.01718 0.00981 -0.1308 0.5148 1.0000
3.250 1.0492 0.01745 0.01009 -0.1292 0.5088 1.0000
3.500 1.0721 0.01766 0.01021 -0.1284 0.5035 1.0000
3.750 1.1009 0.01788 0.01026 -0.1286 0.4988 1.0000
4.000 1.1196 0.01822 0.01061 -0.1272 0.4936 1.0000
4.250 1.1393 0.01850 0.01087 -0.1259 0.4882 1.0000
4.500 1.1632 0.01873 0.01101 -0.1254 0.4834 1.0000
4.750 1.1940 0.01903 0.01114 -0.1261 0.4789 1.0000
5.000 1.2075 0.01941 0.01159 -0.1238 0.4738 1.0000
5.250 1.2271 0.01973 0.01189 -0.1226 0.4689 1.0000
5.500 1.2516 0.02001 0.01208 -0.1222 0.4644 1.0000
5.750 1.2820 0.02037 0.01230 -0.1229 0.4601 1.0000
6.000 1.2929 0.02081 0.01283 -0.1203 0.4555 1.0000
6.250 1.3095 0.02118 0.01320 -0.1186 0.4509 1.0000
6.500 1.3324 0.02151 0.01346 -0.1180 0.4466 1.0000
6.750 1.3694 0.02188 0.01367 -0.1199 0.4424 1.0000
7.000 1.3742 0.02241 0.01432 -0.1163 0.4383 1.0000
7.250 1.3869 0.02291 0.01485 -0.1142 0.4338 1.0000
7.500 1.4071 0.02331 0.01521 -0.1133 0.4295 1.0000
7.750 1.4370 0.02364 0.01544 -0.1139 0.4255 1.0000
8.000 1.4537 0.02424 0.01606 -0.1126 0.4215 1.0000
8.250 1.4598 0.02492 0.01683 -0.1096 0.4171 1.0000
8.500 1.4753 0.02544 0.01736 -0.1081 0.4127 1.0000
8.750 1.4997 0.02581 0.01765 -0.1080 0.4087 1.0000
9.000 1.5297 0.02626 0.01802 -0.1088 0.4047 1.0000
9.250 1.5269 0.02722 0.01914 -0.1048 0.4005 1.0000
9.500 1.5355 0.02798 0.01996 -0.1026 0.3960 1.0000
9.750 1.5548 0.02845 0.02039 -0.1018 0.3918 1.0000
10.000 1.5898 0.02866 0.02046 -0.1032 0.3877 1.0000
10.250 1.5847 0.02991 0.02187 -0.0994 0.3837 1.0000
10.500 1.5863 0.03103 0.02310 -0.0966 0.3792 1.0000
10.750 1.6002 0.03172 0.02380 -0.0953 0.3749 1.0000
11.000 1.6270 0.03198 0.02396 -0.0956 0.3711 1.0000
11.250 1.6329 0.03314 0.02520 -0.0936 0.3668 1.0000
11.500 1.6258 0.03481 0.02701 -0.0903 0.3620 1.0000
11.750 1.6352 0.03578 0.02800 -0.0888 0.3577 1.0000
12.000 1.6585 0.03611 0.02826 -0.0887 0.3539 1.0000
12.250 1.6698 0.03718 0.02937 -0.0875 0.3499 1.0000
12.500 1.6556 0.03955 0.03192 -0.0843 0.3451 1.0000
12.750 1.6614 0.04085 0.03325 -0.0828 0.3407 1.0000
13.000 1.6827 0.04121 0.03356 -0.0825 0.3369 1.0000
13.250 1.6930 0.04240 0.03476 -0.0815 0.3328 1.0000
13.500 1.6730 0.04555 0.03811 -0.0785 0.3278 1.0000
13.750 1.6786 0.04704 0.03965 -0.0773 0.3235 1.0000
14.000 1.7000 0.04740 0.03994 -0.0771 0.3200 1.0000
14.250 1.7114 0.04861 0.04117 -0.0764 0.3163 1.0000
14.500 1.6850 0.05282 0.04560 -0.0738 0.3113 1.0000
14.750 1.6882 0.05471 0.04755 -0.0729 0.3072 1.0000
15.000 1.7096 0.05500 0.04778 -0.0727 0.3038 1.0000
15.250 1.7269 0.05575 0.04850 -0.0723 0.3003 1.0000
15.500 1.6876 0.06170 0.05473 -0.0701 0.2952 1.0000
15.750 1.6873 0.06414 0.05723 -0.0693 0.2913 1.0000
16.000 1.7080 0.06447 0.05753 -0.0692 0.2884 1.0000
16.250 1.7466 0.06312 0.05605 -0.0695 0.2858 1.0000
16.500 1.6832 0.07213 0.06542 -0.0674 0.2806 1.0000
16.750 1.6654 0.07671 0.07014 -0.0668 0.2763 1.0000
17.000 1.6861 0.07695 0.07035 -0.0667 0.2735 1.0000
17.250 1.7216 0.07556 0.06887 -0.0667 0.2712 1.0000
17.500 1.6469 0.08693 0.08059 -0.0659 0.2658 1.0000
17.750 1.5730 0.09916 0.09308 -0.0663 0.2592 1.0000
18.000 1.6130 0.09677 0.09064 -0.0660 0.2579 1.0000
18.250 1.6612 0.09341 0.08719 -0.0657 0.2566 1.0000
18.500 1.7158 0.08939 0.08305 -0.0655 0.2550 1.0000
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