GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 500,000 Max Cl/Cd: 108.28 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe413-il-500000.txt Download as CSV file: xf-goe413-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6427 0.04945 0.04582 -0.0967 0.8972 0.0489
-11.500 -0.6531 0.04456 0.04071 -0.1018 0.8865 0.0487
-11.250 -0.6545 0.04083 0.03668 -0.1047 0.8777 0.0486
-11.000 -0.6482 0.03782 0.03339 -0.1065 0.8705 0.0486
-10.750 -0.6365 0.03535 0.03064 -0.1078 0.8633 0.0487
-10.500 -0.6213 0.03339 0.02838 -0.1085 0.8569 0.0488
-10.250 -0.6027 0.03185 0.02657 -0.1091 0.8509 0.0490
-10.000 -0.5840 0.02987 0.02431 -0.1097 0.8445 0.0494
-9.750 -0.5630 0.02759 0.02193 -0.1099 0.8385 0.0498
-9.500 -0.5392 0.02630 0.02057 -0.1100 0.8324 0.0502
-9.250 -0.5142 0.02517 0.01940 -0.1101 0.8258 0.0505
-9.000 -0.4892 0.02414 0.01828 -0.1102 0.8192 0.0508
-8.750 -0.4639 0.02320 0.01722 -0.1102 0.8131 0.0511
-8.500 -0.4379 0.02226 0.01621 -0.1103 0.8061 0.0515
-8.250 -0.4118 0.02140 0.01523 -0.1103 0.7989 0.0519
-8.000 -0.3853 0.02061 0.01432 -0.1104 0.7917 0.0522
-7.750 -0.3583 0.01983 0.01346 -0.1104 0.7832 0.0526
-7.500 -0.3314 0.01917 0.01266 -0.1104 0.7752 0.0531
-7.250 -0.3036 0.01858 0.01199 -0.1105 0.7660 0.0536
-7.000 -0.2759 0.01810 0.01137 -0.1104 0.7568 0.0541
-6.750 -0.2478 0.01762 0.01079 -0.1105 0.7466 0.0545
-6.500 -0.2199 0.01714 0.01018 -0.1104 0.7359 0.0547
-6.250 -0.1928 0.01609 0.00915 -0.1105 0.7243 0.0553
-6.000 -0.1655 0.01542 0.00845 -0.1104 0.7132 0.0558
-5.750 -0.1375 0.01491 0.00791 -0.1105 0.7017 0.0563
-5.500 -0.1094 0.01449 0.00744 -0.1105 0.6915 0.0569
-5.250 -0.0811 0.01411 0.00701 -0.1106 0.6813 0.0576
-5.000 -0.0527 0.01379 0.00663 -0.1106 0.6723 0.0583
-4.750 -0.0240 0.01350 0.00629 -0.1107 0.6634 0.0592
-4.500 0.0046 0.01327 0.00597 -0.1108 0.6560 0.0599
-4.250 0.0337 0.01303 0.00569 -0.1109 0.6490 0.0604
-4.000 0.0624 0.01268 0.00530 -0.1111 0.6421 0.0611
-3.750 0.0911 0.01233 0.00491 -0.1113 0.6359 0.0621
-3.500 0.1205 0.01205 0.00464 -0.1115 0.6301 0.0631
-3.250 0.1497 0.01185 0.00441 -0.1117 0.6242 0.0642
-3.000 0.1789 0.01173 0.00421 -0.1118 0.6184 0.0653
-2.750 0.2085 0.01157 0.00404 -0.1120 0.6133 0.0666
-2.500 0.2381 0.01135 0.00382 -0.1123 0.6077 0.0685
-2.250 0.2674 0.01121 0.00364 -0.1125 0.6022 0.0707
-2.000 0.2968 0.01115 0.00352 -0.1126 0.5968 0.0732
-1.750 0.3266 0.01098 0.00339 -0.1128 0.5922 0.0780
-1.500 0.3561 0.01057 0.00326 -0.1133 0.5874 0.1351
-1.250 0.3856 0.01047 0.00323 -0.1135 0.5827 0.1703
-1.000 0.4149 0.01046 0.00326 -0.1137 0.5778 0.1928
-0.750 0.4446 0.01036 0.00325 -0.1139 0.5737 0.2131
-0.500 0.4742 0.01029 0.00325 -0.1141 0.5692 0.2308
-0.250 0.5036 0.01025 0.00325 -0.1143 0.5647 0.2506
0.000 0.5329 0.01025 0.00328 -0.1145 0.5600 0.2732
0.250 0.5623 0.01023 0.00332 -0.1147 0.5558 0.2984
0.500 0.5919 0.01016 0.00337 -0.1149 0.5514 0.3267
0.750 0.6213 0.01011 0.00341 -0.1151 0.5468 0.3559
1.250 0.6796 0.01015 0.00352 -0.1154 0.5375 0.4093
1.500 0.7090 0.01008 0.00358 -0.1156 0.5331 0.4386
1.750 0.7382 0.01003 0.00365 -0.1157 0.5282 0.4753
2.000 0.7671 0.01002 0.00373 -0.1158 0.5233 0.5211
2.250 0.7959 0.01006 0.00384 -0.1159 0.5179 0.5623
2.500 0.8248 0.01000 0.00391 -0.1160 0.5118 0.5995
2.750 0.8532 0.00995 0.00396 -0.1159 0.5051 0.6389
3.000 0.8810 0.00992 0.00408 -0.1158 0.4991 0.6904
3.250 0.9079 0.00979 0.00420 -0.1154 0.4927 0.7703
3.500 0.9307 0.00967 0.00428 -0.1139 0.4858 0.8573
3.750 0.9533 0.00955 0.00428 -0.1124 0.4791 1.0000
4.000 0.9823 0.00965 0.00436 -0.1125 0.4717 1.0000
4.250 1.0104 0.00982 0.00445 -0.1125 0.4646 1.0000
4.500 1.0391 0.00994 0.00456 -0.1126 0.4570 1.0000
4.750 1.0669 0.01011 0.00467 -0.1126 0.4479 1.0000
5.000 1.0949 0.01026 0.00480 -0.1126 0.4395 1.0000
5.250 1.1222 0.01046 0.00494 -0.1125 0.4298 1.0000
5.500 1.1497 0.01065 0.00510 -0.1124 0.4200 1.0000
6.000 1.2030 0.01111 0.00546 -0.1121 0.3987 1.0000
6.250 1.2288 0.01139 0.00568 -0.1118 0.3873 1.0000
6.500 1.2542 0.01170 0.00593 -0.1114 0.3759 1.0000
6.750 1.2800 0.01198 0.00617 -0.1111 0.3655 1.0000
7.000 1.3044 0.01233 0.00646 -0.1107 0.3551 1.0000
7.250 1.3292 0.01265 0.00676 -0.1102 0.3443 1.0000
7.500 1.3530 0.01303 0.00708 -0.1097 0.3327 1.0000
7.750 1.3754 0.01348 0.00746 -0.1089 0.3212 1.0000
8.000 1.3986 0.01385 0.00781 -0.1083 0.3098 1.0000
8.250 1.4206 0.01429 0.00821 -0.1075 0.2984 1.0000
8.500 1.4406 0.01481 0.00866 -0.1065 0.2854 1.0000
8.750 1.4590 0.01541 0.00918 -0.1052 0.2690 1.0000
9.000 1.4745 0.01606 0.00976 -0.1036 0.2514 1.0000
9.250 1.4856 0.01691 0.01049 -0.1013 0.2295 1.0000
9.500 1.4896 0.01825 0.01163 -0.0985 0.1985 1.0000
9.750 1.4858 0.02021 0.01334 -0.0953 0.1597 1.0000
10.000 1.4688 0.02333 0.01611 -0.0916 0.1069 1.0000
10.250 1.4661 0.02563 0.01829 -0.0894 0.0894 1.0000
10.500 1.4720 0.02734 0.02000 -0.0879 0.0840 1.0000
10.750 1.4781 0.02908 0.02176 -0.0866 0.0810 1.0000
11.000 1.4835 0.03093 0.02363 -0.0853 0.0787 1.0000
11.250 1.4918 0.03259 0.02535 -0.0843 0.0774 1.0000
11.500 1.4986 0.03440 0.02722 -0.0833 0.0762 1.0000
11.750 1.5038 0.03640 0.02927 -0.0824 0.0751 1.0000
12.000 1.5075 0.03860 0.03153 -0.0815 0.0742 1.0000
12.250 1.5096 0.04102 0.03400 -0.0806 0.0734 1.0000
12.500 1.5101 0.04365 0.03669 -0.0798 0.0726 1.0000
12.750 1.5090 0.04653 0.03964 -0.0792 0.0718 1.0000
13.000 1.5062 0.04967 0.04285 -0.0786 0.0711 1.0000
13.250 1.5081 0.05235 0.04560 -0.0781 0.0707 1.0000
13.500 1.5106 0.05501 0.04834 -0.0778 0.0703 1.0000
13.750 1.5125 0.05777 0.05117 -0.0774 0.0699 1.0000
14.000 1.5140 0.06056 0.05403 -0.0771 0.0694 1.0000
14.250 1.5146 0.06351 0.05706 -0.0769 0.0689 1.0000
14.500 1.5150 0.06650 0.06012 -0.0767 0.0685 1.0000
14.750 1.5155 0.06950 0.06318 -0.0765 0.0681 1.0000
15.000 1.5153 0.07259 0.06634 -0.0764 0.0678 1.0000
15.250 1.5160 0.07559 0.06940 -0.0763 0.0674 1.0000
15.500 1.5161 0.07870 0.07257 -0.0763 0.0671 1.0000
15.750 1.5172 0.08166 0.07558 -0.0762 0.0667 1.0000
16.000 1.5181 0.08465 0.07863 -0.0762 0.0664 1.0000
16.250 1.5196 0.08756 0.08159 -0.0762 0.0661 1.0000
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