GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 200,000 Max Cl/Cd: 75.29 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe413-il-200000.txt Download as CSV file: xf-goe413-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4038 0.04751 0.04298 -0.1123 0.9118 0.0820
-9.000 -0.3957 0.04401 0.03933 -0.1133 0.9003 0.0803
-8.750 -0.3931 0.03939 0.03437 -0.1153 0.8898 0.0786
-8.500 -0.3922 0.03361 0.02781 -0.1177 0.8785 0.0762
-8.250 -0.3771 0.03076 0.02441 -0.1181 0.8685 0.0756
-8.000 -0.3561 0.02918 0.02261 -0.1177 0.8588 0.0760
-7.750 -0.3338 0.02781 0.02103 -0.1174 0.8495 0.0764
-7.500 -0.3106 0.02647 0.01947 -0.1171 0.8398 0.0768
-7.250 -0.2865 0.02525 0.01802 -0.1167 0.8313 0.0770
-7.000 -0.2616 0.02415 0.01674 -0.1165 0.8211 0.0773
-6.750 -0.2361 0.02319 0.01559 -0.1160 0.8132 0.0777
-6.500 -0.2100 0.02231 0.01459 -0.1158 0.8026 0.0782
-6.250 -0.1836 0.02152 0.01364 -0.1154 0.7951 0.0789
-6.000 -0.1566 0.02085 0.01287 -0.1153 0.7851 0.0799
-5.750 -0.1293 0.02022 0.01210 -0.1150 0.7773 0.0808
-5.500 -0.1020 0.01963 0.01142 -0.1148 0.7689 0.0816
-5.250 -0.0751 0.01881 0.01064 -0.1145 0.7603 0.0826
-5.000 -0.0478 0.01821 0.01000 -0.1142 0.7539 0.0837
-4.750 -0.0201 0.01772 0.00956 -0.1143 0.7448 0.0850
-4.500 0.0079 0.01725 0.00904 -0.1141 0.7379 0.0865
-4.250 0.0361 0.01687 0.00861 -0.1141 0.7311 0.0883
-4.000 0.0643 0.01645 0.00819 -0.1141 0.7231 0.0906
-3.750 0.0929 0.01604 0.00776 -0.1142 0.7170 0.0936
-3.500 0.1217 0.01577 0.00747 -0.1143 0.7103 0.0971
-3.250 0.1505 0.01544 0.00717 -0.1144 0.7032 0.1018
-3.000 0.1797 0.01514 0.00685 -0.1145 0.6975 0.1103
-2.750 0.2087 0.01485 0.00671 -0.1147 0.6910 0.1354
-2.500 0.2378 0.01462 0.00664 -0.1149 0.6843 0.1804
-2.250 0.2671 0.01453 0.00655 -0.1150 0.6787 0.2102
-2.000 0.2961 0.01454 0.00658 -0.1151 0.6727 0.2317
-1.750 0.3250 0.01454 0.00659 -0.1152 0.6660 0.2490
-1.500 0.3542 0.01452 0.00652 -0.1152 0.6603 0.2638
-1.250 0.3833 0.01458 0.00653 -0.1152 0.6546 0.2800
-1.000 0.4119 0.01456 0.00659 -0.1153 0.6479 0.2964
-0.750 0.4409 0.01453 0.00658 -0.1154 0.6422 0.3143
-0.500 0.4702 0.01459 0.00660 -0.1154 0.6371 0.3355
-0.250 0.4985 0.01459 0.00671 -0.1155 0.6309 0.3581
0.000 0.5273 0.01458 0.00676 -0.1156 0.6250 0.3842
0.250 0.5563 0.01455 0.00679 -0.1156 0.6199 0.4138
0.500 0.5847 0.01461 0.00693 -0.1156 0.6145 0.4467
0.750 0.6127 0.01459 0.00710 -0.1156 0.6084 0.4825
1.000 0.6412 0.01461 0.00722 -0.1155 0.6029 0.5248
1.250 0.6700 0.01470 0.00733 -0.1154 0.5980 0.5695
1.500 0.6967 0.01470 0.00754 -0.1151 0.5919 0.6118
2.000 0.7492 0.01456 0.00775 -0.1138 0.5809 0.7130
2.250 0.7719 0.01455 0.00793 -0.1122 0.5757 0.7898
2.500 0.7886 0.01438 0.00803 -0.1092 0.5696 0.8947
2.750 0.8212 0.01436 0.00796 -0.1099 0.5637 1.0000
3.000 0.8519 0.01457 0.00800 -0.1103 0.5586 1.0000
3.250 0.8794 0.01477 0.00822 -0.1104 0.5517 1.0000
3.500 0.9082 0.01491 0.00831 -0.1105 0.5453 1.0000
3.750 0.9381 0.01507 0.00833 -0.1107 0.5399 1.0000
4.000 0.9650 0.01526 0.00854 -0.1106 0.5324 1.0000
4.250 0.9932 0.01534 0.00856 -0.1105 0.5248 1.0000
4.500 1.0218 0.01547 0.00858 -0.1105 0.5178 1.0000
4.750 1.0480 0.01557 0.00871 -0.1102 0.5088 1.0000
5.000 1.0765 0.01565 0.00866 -0.1101 0.5017 1.0000
5.250 1.1023 0.01584 0.00890 -0.1098 0.4932 1.0000
5.500 1.1295 0.01594 0.00895 -0.1095 0.4853 1.0000
5.750 1.1557 0.01612 0.00910 -0.1092 0.4769 1.0000
6.000 1.1816 0.01625 0.00923 -0.1088 0.4680 1.0000
6.250 1.2079 0.01646 0.00938 -0.1085 0.4602 1.0000
6.500 1.2328 0.01666 0.00961 -0.1080 0.4510 1.0000
6.750 1.2584 0.01688 0.00976 -0.1076 0.4427 1.0000
7.000 1.2823 0.01711 0.01003 -0.1070 0.4331 1.0000
7.250 1.3072 0.01739 0.01025 -0.1065 0.4251 1.0000
7.500 1.3303 0.01767 0.01058 -0.1058 0.4155 1.0000
7.750 1.3538 0.01799 0.01084 -0.1052 0.4067 1.0000
8.000 1.3755 0.01831 0.01118 -0.1043 0.3963 1.0000
8.250 1.3974 0.01869 0.01155 -0.1034 0.3873 1.0000
8.500 1.4183 0.01908 0.01194 -0.1025 0.3780 1.0000
8.750 1.4387 0.01953 0.01238 -0.1014 0.3693 1.0000
9.000 1.4574 0.01999 0.01284 -0.1002 0.3596 1.0000
9.250 1.4750 0.02050 0.01337 -0.0988 0.3500 1.0000
9.500 1.4910 0.02107 0.01390 -0.0972 0.3410 1.0000
9.750 1.5049 0.02164 0.01454 -0.0954 0.3321 1.0000
10.000 1.5162 0.02237 0.01521 -0.0933 0.3226 1.0000
10.250 1.5277 0.02314 0.01606 -0.0914 0.3122 1.0000
10.500 1.5365 0.02410 0.01701 -0.0894 0.3015 1.0000
10.750 1.5433 0.02525 0.01815 -0.0874 0.2893 1.0000
11.000 1.5506 0.02649 0.01944 -0.0857 0.2763 1.0000
11.250 1.5550 0.02800 0.02096 -0.0840 0.2617 1.0000
11.500 1.5559 0.02988 0.02281 -0.0822 0.2442 1.0000
11.750 1.5512 0.03232 0.02518 -0.0803 0.2236 1.0000
12.000 1.5429 0.03524 0.02801 -0.0786 0.1977 1.0000
12.250 1.5279 0.03895 0.03158 -0.0769 0.1702 1.0000
12.500 1.5107 0.04309 0.03559 -0.0755 0.1467 1.0000
12.750 1.4956 0.04725 0.03965 -0.0745 0.1306 1.0000
13.000 1.4849 0.05114 0.04352 -0.0738 0.1212 1.0000
13.250 1.4760 0.05498 0.04736 -0.0733 0.1156 1.0000
13.500 1.4707 0.05851 0.05092 -0.0729 0.1116 1.0000
13.750 1.4646 0.06218 0.05462 -0.0726 0.1087 1.0000
14.000 1.4575 0.06601 0.05847 -0.0724 0.1065 1.0000
14.250 1.4568 0.06909 0.06161 -0.0721 0.1046 1.0000
14.500 1.4564 0.07217 0.06474 -0.0720 0.1029 1.0000
14.750 1.4567 0.07515 0.06778 -0.0718 0.1014 1.0000
15.000 1.4573 0.07809 0.07075 -0.0716 0.1000 1.0000
15.250 1.4592 0.08080 0.07347 -0.0713 0.0988 1.0000
15.500 1.4627 0.08319 0.07583 -0.0709 0.0975 1.0000
15.750 1.4699 0.08501 0.07761 -0.0702 0.0963 1.0000
16.000 1.4770 0.08711 0.07978 -0.0699 0.0954 1.0000
16.250 1.4848 0.08906 0.08179 -0.0696 0.0944 1.0000
16.500 1.4936 0.09084 0.08362 -0.0692 0.0935 1.0000
16.750 1.5033 0.09245 0.08527 -0.0687 0.0927 1.0000
17.000 1.5138 0.09392 0.08678 -0.0681 0.0919 1.0000
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Polar data table (+)
Polar graphs
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