GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 386 AIRFOIL (goe386-il) Reynolds number: 200,000 Max Cl/Cd: 61.72 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe386-il-200000.txt Download as CSV file: xf-goe386-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 386 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0530 0.10848 0.10466 -0.0830 0.9541 0.1077
-10.750 -0.3217 0.05577 0.05136 -0.1265 0.9374 0.0896
-10.500 -0.3236 0.05149 0.04696 -0.1280 0.9248 0.0887
-10.250 -0.3437 0.04698 0.04221 -0.1274 0.9094 0.0880
-10.000 -0.3681 0.04243 0.03727 -0.1254 0.8914 0.0873
-9.750 -0.3784 0.03892 0.03336 -0.1232 0.8741 0.0873
-9.500 -0.3790 0.03614 0.03017 -0.1210 0.8572 0.0877
-9.250 -0.3729 0.03386 0.02746 -0.1190 0.8407 0.0883
-9.000 -0.3616 0.03200 0.02517 -0.1173 0.8242 0.0888
-8.750 -0.3468 0.03052 0.02326 -0.1157 0.8073 0.0893
-8.500 -0.3278 0.02867 0.02124 -0.1147 0.7894 0.0900
-8.250 -0.3056 0.02740 0.01984 -0.1140 0.7727 0.0909
-8.000 -0.2819 0.02647 0.01880 -0.1134 0.7579 0.0921
-7.750 -0.2582 0.02561 0.01774 -0.1128 0.7453 0.0934
-7.500 -0.2355 0.02478 0.01672 -0.1121 0.7326 0.0946
-7.250 -0.2114 0.02400 0.01564 -0.1114 0.7232 0.0958
-7.000 -0.1877 0.02332 0.01475 -0.1107 0.7131 0.0967
-6.750 -0.1620 0.02245 0.01372 -0.1104 0.7053 0.0979
-6.500 -0.1359 0.02176 0.01306 -0.1102 0.6977 0.0994
-6.250 -0.1099 0.02126 0.01252 -0.1098 0.6905 0.1012
-6.000 -0.0831 0.02080 0.01193 -0.1096 0.6844 0.1029
-5.750 -0.0567 0.02038 0.01140 -0.1092 0.6784 0.1045
-5.500 -0.0305 0.01993 0.01088 -0.1088 0.6722 0.1059
-5.250 -0.0041 0.01942 0.01043 -0.1086 0.6670 0.1079
-5.000 0.0233 0.01915 0.01012 -0.1085 0.6626 0.1103
-4.750 0.0499 0.01890 0.00984 -0.1082 0.6582 0.1128
-4.500 0.0760 0.01861 0.00955 -0.1078 0.6535 0.1151
-4.250 0.1020 0.01831 0.00931 -0.1074 0.6486 0.1178
-4.000 0.1290 0.01813 0.00908 -0.1071 0.6435 0.1213
-3.750 0.1561 0.01800 0.00890 -0.1069 0.6384 0.1254
-3.500 0.1813 0.01782 0.00881 -0.1063 0.6331 0.1302
-3.250 0.2078 0.01767 0.00868 -0.1060 0.6282 0.1363
-3.000 0.2351 0.01754 0.00855 -0.1057 0.6236 0.1452
-2.750 0.2632 0.01750 0.00850 -0.1056 0.6191 0.1597
-2.500 0.2883 0.01737 0.00853 -0.1051 0.6143 0.1807
-2.250 0.3145 0.01734 0.00854 -0.1047 0.6091 0.2051
-2.000 0.3416 0.01731 0.00854 -0.1044 0.6046 0.2246
-1.750 0.3698 0.01737 0.00856 -0.1044 0.6008 0.2412
-1.500 0.3984 0.01747 0.00866 -0.1045 0.5972 0.2557
-1.250 0.4239 0.01749 0.00876 -0.1041 0.5933 0.2682
-1.000 0.4498 0.01752 0.00883 -0.1036 0.5888 0.2805
-0.750 0.4764 0.01747 0.00885 -0.1033 0.5843 0.2927
-0.500 0.5044 0.01748 0.00882 -0.1033 0.5801 0.3076
-0.250 0.5331 0.01751 0.00886 -0.1034 0.5764 0.3242
0.000 0.5583 0.01752 0.00900 -0.1029 0.5724 0.3440
0.250 0.5826 0.01745 0.00909 -0.1022 0.5677 0.3712
0.500 0.6076 0.01729 0.00913 -0.1017 0.5630 0.4150
0.750 0.6328 0.01701 0.00912 -0.1012 0.5585 0.4932
1.000 0.6563 0.01667 0.00924 -0.1001 0.5544 0.6303
1.250 0.6730 0.01638 0.00955 -0.0971 0.5496 0.7865
1.500 0.7069 0.01639 0.00979 -0.0973 0.5439 0.9045
1.750 0.7580 0.01650 0.00982 -0.1014 0.5383 0.9610
2.000 0.8233 0.01670 0.00982 -0.1086 0.5326 0.9875
2.250 0.8718 0.01678 0.00992 -0.1129 0.5253 1.0000
2.500 0.8906 0.01680 0.00987 -0.1113 0.5195 1.0000
2.750 0.9134 0.01684 0.00975 -0.1103 0.5143 1.0000
3.000 0.9295 0.01697 0.00988 -0.1082 0.5079 1.0000
3.250 0.9467 0.01702 0.00990 -0.1062 0.5010 1.0000
3.500 0.9687 0.01705 0.00980 -0.1050 0.4951 1.0000
3.750 0.9860 0.01718 0.00991 -0.1030 0.4881 1.0000
4.000 1.0028 0.01725 0.00995 -0.1009 0.4803 1.0000
4.250 1.0263 0.01731 0.00985 -0.1000 0.4738 1.0000
4.500 1.0394 0.01746 0.01006 -0.0973 0.4646 1.0000
4.750 1.0594 0.01753 0.01002 -0.0958 0.4569 1.0000
5.000 1.0760 0.01773 0.01019 -0.0938 0.4480 1.0000
5.250 1.0941 0.01787 0.01027 -0.0921 0.4397 1.0000
5.500 1.1127 0.01812 0.01045 -0.0905 0.4317 1.0000
5.750 1.1294 0.01836 0.01066 -0.0886 0.4235 1.0000
6.000 1.1504 0.01864 0.01080 -0.0874 0.4168 1.0000
6.250 1.1653 0.01898 0.01117 -0.0853 0.4092 1.0000
6.500 1.1837 0.01928 0.01137 -0.0838 0.4030 1.0000
6.750 1.2011 0.01967 0.01171 -0.0822 0.3969 1.0000
7.000 1.2161 0.02007 0.01211 -0.0802 0.3908 1.0000
7.250 1.2362 0.02046 0.01240 -0.0791 0.3856 1.0000
7.500 1.2570 0.02093 0.01280 -0.0782 0.3808 1.0000
7.750 1.2730 0.02144 0.01335 -0.0766 0.3760 1.0000
8.000 1.2917 0.02192 0.01382 -0.0754 0.3717 1.0000
8.250 1.3161 0.02238 0.01416 -0.0752 0.3677 1.0000
8.500 1.3379 0.02293 0.01468 -0.0746 0.3637 1.0000
8.750 1.3521 0.02355 0.01537 -0.0729 0.3598 1.0000
9.000 1.3699 0.02412 0.01595 -0.0717 0.3560 1.0000
9.250 1.3912 0.02466 0.01645 -0.0711 0.3526 1.0000
9.500 1.4228 0.02514 0.01680 -0.0720 0.3491 1.0000
9.750 1.4373 0.02587 0.01760 -0.0705 0.3461 1.0000
10.000 1.4481 0.02664 0.01846 -0.0686 0.3426 1.0000
10.250 1.4628 0.02732 0.01918 -0.0672 0.3389 1.0000
10.500 1.4826 0.02790 0.01972 -0.0665 0.3353 1.0000
10.750 1.5173 0.02835 0.02003 -0.0678 0.3316 1.0000
11.000 1.5242 0.02931 0.02111 -0.0656 0.3288 1.0000
11.250 1.5294 0.03032 0.02224 -0.0633 0.3256 1.0000
11.500 1.5400 0.03121 0.02317 -0.0617 0.3221 1.0000
11.750 1.5576 0.03187 0.02382 -0.0609 0.3186 1.0000
12.000 1.5876 0.03230 0.02415 -0.0615 0.3153 1.0000
12.250 1.6018 0.03330 0.02521 -0.0604 0.3125 1.0000
12.500 1.6011 0.03470 0.02677 -0.0579 0.3100 1.0000
12.750 1.6052 0.03602 0.02821 -0.0560 0.3073 1.0000
13.000 1.6147 0.03715 0.02940 -0.0547 0.3045 1.0000
13.250 1.6315 0.03796 0.03022 -0.0540 0.3018 1.0000
13.500 1.6592 0.03835 0.03056 -0.0544 0.2991 1.0000
13.750 1.6847 0.03911 0.03129 -0.0546 0.2963 1.0000
14.000 1.6677 0.04146 0.03387 -0.0512 0.2939 1.0000
14.250 1.6575 0.04374 0.03633 -0.0488 0.2910 1.0000
14.500 1.6569 0.04559 0.03828 -0.0473 0.2880 1.0000
14.750 1.6698 0.04661 0.03932 -0.0466 0.2851 1.0000
15.000 1.7007 0.04657 0.03919 -0.0470 0.2822 1.0000
15.250 1.7156 0.04775 0.04039 -0.0465 0.2793 1.0000
15.500 1.6774 0.05220 0.04514 -0.0435 0.2763 1.0000
15.750 1.6531 0.05623 0.04936 -0.0418 0.2729 1.0000
16.000 1.6542 0.05833 0.05153 -0.0411 0.2697 1.0000
16.250 1.6806 0.05824 0.05139 -0.0410 0.2669 1.0000
16.500 1.7304 0.05650 0.04949 -0.0417 0.2641 1.0000
16.750 1.6462 0.06621 0.05966 -0.0394 0.2601 1.0000
17.000 1.5929 0.07434 0.06805 -0.0392 0.2551 1.0000
17.250 1.6150 0.07442 0.06810 -0.0390 0.2523 1.0000
17.500 1.6631 0.07171 0.06526 -0.0388 0.2500 1.0000
17.750 1.4478 0.10080 0.09504 -0.0422 0.2377 1.0000
18.000 1.5051 0.09598 0.09014 -0.0411 0.2370 1.0000
18.250 1.5661 0.09089 0.08493 -0.0401 0.2358 1.0000
18.500 1.6324 0.08537 0.07923 -0.0392 0.2342 1.0000
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Polar data table (+)
Polar graphs
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