GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 200,000 Max Cl/Cd: 64.78 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe628-il-200000.txt Download as CSV file: xf-goe628-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4135 0.06263 0.05899 -0.0902 0.9762 0.0841
-10.250 -0.4572 0.04602 0.04187 -0.1127 0.9543 0.0821
-10.000 -0.4587 0.03933 0.03457 -0.1189 0.9413 0.0822
-9.750 -0.4359 0.03509 0.02976 -0.1236 0.9356 0.0830
-9.500 -0.4174 0.03262 0.02688 -0.1244 0.9246 0.0834
-9.250 -0.3877 0.03027 0.02414 -0.1266 0.9187 0.0839
-9.000 -0.3638 0.02816 0.02192 -0.1270 0.9089 0.0849
-8.750 -0.3325 0.02664 0.02030 -0.1282 0.9018 0.0859
-8.500 -0.3066 0.02540 0.01890 -0.1282 0.8922 0.0866
-8.250 -0.2783 0.02420 0.01755 -0.1285 0.8834 0.0874
-8.000 -0.2534 0.02322 0.01640 -0.1281 0.8734 0.0882
-7.750 -0.2259 0.02230 0.01534 -0.1280 0.8644 0.0894
-7.500 -0.2014 0.02154 0.01443 -0.1273 0.8542 0.0906
-7.250 -0.1743 0.02077 0.01348 -0.1270 0.8453 0.0917
-7.000 -0.1496 0.02013 0.01270 -0.1262 0.8354 0.0926
-6.750 -0.1228 0.01941 0.01185 -0.1258 0.8267 0.0935
-6.500 -0.0982 0.01866 0.01111 -0.1251 0.8174 0.0949
-6.250 -0.0721 0.01809 0.01053 -0.1246 0.8086 0.0965
-6.000 -0.0466 0.01766 0.01005 -0.1240 0.8000 0.0986
-5.750 -0.0209 0.01725 0.00957 -0.1233 0.7910 0.1010
-5.500 0.0057 0.01691 0.00910 -0.1228 0.7829 0.1034
-5.250 0.0295 0.01639 0.00863 -0.1219 0.7733 0.1064
-5.000 0.0555 0.01603 0.00822 -0.1212 0.7642 0.1102
-4.750 0.0804 0.01571 0.00783 -0.1203 0.7536 0.1152
-4.500 0.1054 0.01532 0.00744 -0.1196 0.7446 0.1237
-4.250 0.1298 0.01491 0.00709 -0.1187 0.7354 0.1410
-4.000 0.1558 0.01450 0.00689 -0.1183 0.7281 0.1921
-3.750 0.1806 0.01451 0.00697 -0.1175 0.7191 0.2292
-3.500 0.2090 0.01463 0.00697 -0.1172 0.7117 0.2504
-3.250 0.2346 0.01475 0.00708 -0.1165 0.7033 0.2647
-3.000 0.2615 0.01482 0.00709 -0.1160 0.6952 0.2770
-2.750 0.2890 0.01498 0.00711 -0.1155 0.6878 0.2898
-2.500 0.3143 0.01505 0.00724 -0.1148 0.6792 0.3008
-2.250 0.3426 0.01512 0.00717 -0.1145 0.6723 0.3114
-2.000 0.3674 0.01517 0.00726 -0.1136 0.6636 0.3204
-1.750 0.3943 0.01518 0.00718 -0.1131 0.6556 0.3304
-1.500 0.4205 0.01523 0.00722 -0.1125 0.6477 0.3394
-1.250 0.4464 0.01523 0.00716 -0.1118 0.6391 0.3490
-1.000 0.4740 0.01526 0.00716 -0.1114 0.6320 0.3586
-0.750 0.4983 0.01527 0.00715 -0.1105 0.6225 0.3688
-0.500 0.5257 0.01528 0.00712 -0.1101 0.6148 0.3794
-0.250 0.5496 0.01526 0.00711 -0.1091 0.6049 0.3895
0.000 0.5764 0.01524 0.00704 -0.1086 0.5966 0.3997
0.250 0.6006 0.01521 0.00701 -0.1077 0.5868 0.4087
0.500 0.6272 0.01516 0.00691 -0.1072 0.5782 0.4171
0.750 0.6512 0.01516 0.00688 -0.1062 0.5676 0.4260
1.000 0.6777 0.01511 0.00678 -0.1057 0.5585 0.4349
1.250 0.7006 0.01511 0.00678 -0.1046 0.5468 0.4446
1.500 0.7255 0.01508 0.00674 -0.1038 0.5367 0.4538
1.750 0.7493 0.01509 0.00673 -0.1029 0.5256 0.4649
2.000 0.7728 0.01511 0.00678 -0.1019 0.5147 0.4765
2.250 0.7972 0.01515 0.00676 -0.1011 0.5044 0.4890
2.500 0.8193 0.01520 0.00686 -0.0999 0.4926 0.5034
2.750 0.8427 0.01527 0.00692 -0.0989 0.4822 0.5210
3.000 0.8645 0.01529 0.00702 -0.0977 0.4714 0.5425
3.250 0.8863 0.01532 0.00717 -0.0965 0.4617 0.5754
3.500 0.9069 0.01512 0.00731 -0.0950 0.4527 0.6775
3.750 0.9659 0.01506 0.00762 -0.1013 0.4409 1.0000
4.000 0.9896 0.01538 0.00776 -0.1005 0.4331 1.0000
4.250 1.0114 0.01568 0.00802 -0.0994 0.4249 1.0000
4.500 1.0341 0.01598 0.00822 -0.0984 0.4177 1.0000
4.750 1.0579 0.01636 0.00849 -0.0977 0.4113 1.0000
5.000 1.0795 0.01667 0.00879 -0.0965 0.4048 1.0000
5.250 1.1032 0.01703 0.00905 -0.0958 0.3992 1.0000
5.500 1.1272 0.01744 0.00939 -0.0952 0.3937 1.0000
5.750 1.1480 0.01777 0.00974 -0.0939 0.3880 1.0000
6.000 1.1707 0.01812 0.01003 -0.0930 0.3828 1.0000
6.250 1.1979 0.01862 0.01040 -0.0931 0.3782 1.0000
6.500 1.2172 0.01898 0.01084 -0.0916 0.3737 1.0000
6.750 1.2387 0.01936 0.01123 -0.0906 0.3692 1.0000
7.000 1.2620 0.01976 0.01159 -0.0899 0.3650 1.0000
7.250 1.2906 0.02033 0.01203 -0.0903 0.3607 1.0000
7.500 1.3072 0.02071 0.01253 -0.0884 0.3568 1.0000
7.750 1.3273 0.02114 0.01300 -0.0872 0.3528 1.0000
8.000 1.3497 0.02158 0.01343 -0.0864 0.3491 1.0000
8.250 1.3759 0.02208 0.01386 -0.0864 0.3455 1.0000
8.500 1.3987 0.02267 0.01447 -0.0858 0.3418 1.0000
8.750 1.4137 0.02314 0.01505 -0.0838 0.3382 1.0000
9.000 1.4323 0.02362 0.01558 -0.0825 0.3347 1.0000
9.250 1.4539 0.02408 0.01604 -0.0816 0.3311 1.0000
9.500 1.4822 0.02465 0.01652 -0.0820 0.3274 1.0000
9.750 1.4983 0.02527 0.01723 -0.0804 0.3240 1.0000
10.000 1.5057 0.02576 0.01784 -0.0772 0.3203 1.0000
10.250 1.5185 0.02623 0.01837 -0.0750 0.3165 1.0000
10.500 1.5386 0.02668 0.01880 -0.0740 0.3130 1.0000
10.750 1.5749 0.02741 0.01941 -0.0759 0.3089 1.0000
11.000 1.5737 0.02801 0.02020 -0.0715 0.3062 1.0000
11.250 1.5787 0.02867 0.02100 -0.0684 0.3030 1.0000
11.500 1.5899 0.02929 0.02168 -0.0663 0.2995 1.0000
11.750 1.6082 0.02982 0.02223 -0.0652 0.2963 1.0000
12.000 1.6403 0.03039 0.02271 -0.0662 0.2928 1.0000
12.250 1.6418 0.03130 0.02378 -0.0630 0.2898 1.0000
12.500 1.6401 0.03226 0.02491 -0.0595 0.2867 1.0000
12.750 1.6456 0.03311 0.02586 -0.0571 0.2832 1.0000
13.000 1.6601 0.03375 0.02653 -0.0558 0.2799 1.0000
13.250 1.6893 0.03415 0.02685 -0.0563 0.2764 1.0000
13.500 1.6883 0.03542 0.02827 -0.0535 0.2733 1.0000
13.750 1.6787 0.03693 0.02997 -0.0500 0.2700 1.0000
14.000 1.6797 0.03814 0.03129 -0.0478 0.2664 1.0000
14.250 1.6930 0.03883 0.03200 -0.0467 0.2629 1.0000
14.500 1.7229 0.03907 0.03212 -0.0471 0.2589 1.0000
14.750 1.6990 0.04156 0.03489 -0.0434 0.2558 1.0000
15.000 1.6878 0.04369 0.03718 -0.0411 0.2518 1.0000
15.250 1.6931 0.04489 0.03842 -0.0399 0.2479 1.0000
15.500 1.7216 0.04476 0.03816 -0.0399 0.2437 1.0000
15.750 1.6969 0.04819 0.04185 -0.0376 0.2403 1.0000
16.000 1.6807 0.05129 0.04514 -0.0362 0.2362 1.0000
16.250 1.6845 0.05287 0.04675 -0.0354 0.2321 1.0000
16.500 1.7121 0.05259 0.04633 -0.0352 0.2279 1.0000
16.750 1.6758 0.05794 0.05200 -0.0341 0.2241 1.0000
17.000 1.6613 0.06164 0.05583 -0.0338 0.2196 1.0000
17.250 1.6727 0.06265 0.05681 -0.0335 0.2152 1.0000
17.500 1.6650 0.06593 0.06018 -0.0334 0.2109 1.0000
17.750 1.6367 0.07175 0.06621 -0.0340 0.2062 1.0000
18.000 1.6413 0.07372 0.06818 -0.0341 0.2014 1.0000
18.250 1.6403 0.07650 0.07097 -0.0343 0.1969 1.0000
18.500 1.6056 0.08387 0.07857 -0.0360 0.1920 1.0000
18.750 1.6095 0.08615 0.08085 -0.0364 0.1874 1.0000
19.000 1.6077 0.08924 0.08396 -0.0370 0.1828 1.0000
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Polar data table (+)
Polar graphs
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