GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 200,000 Max Cl/Cd: 80.02 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe381-il-200000.txt Download as CSV file: xf-goe381-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2907 0.10503 0.10184 -0.0247 1.0000 0.0224
-7.750 -0.2895 0.10332 0.10020 -0.0262 1.0000 0.0225
-7.500 -0.2912 0.10183 0.09877 -0.0267 1.0000 0.0225
-6.250 -0.2862 0.08778 0.08492 -0.0254 0.9970 0.0230
-6.000 -0.2675 0.08246 0.07961 -0.0268 0.9941 0.0236
-5.750 -0.2414 0.07804 0.07516 -0.0316 0.9891 0.0243
-5.500 -0.2082 0.07362 0.07071 -0.0386 0.9846 0.0252
-5.250 -0.1741 0.06942 0.06646 -0.0457 0.9791 0.0266
-5.000 -0.1323 0.06531 0.06225 -0.0543 0.9734 0.0292
-4.750 -0.0542 0.06270 0.05935 -0.0711 0.9695 0.0311
-4.500 -0.0172 0.05849 0.05502 -0.0767 0.9623 0.0314
-4.250 0.0030 0.05181 0.04840 -0.0795 0.9586 0.0327
-4.000 0.0398 0.04793 0.04447 -0.0843 0.9555 0.0344
-3.750 0.0735 0.04486 0.04130 -0.0880 0.9469 0.0370
-3.500 0.1397 0.04386 0.03977 -0.0956 0.9419 0.0425
-3.250 0.1556 0.03836 0.03438 -0.0969 0.9324 0.0447
-3.000 0.1857 0.03579 0.03173 -0.0986 0.9247 0.0482
-2.750 0.2307 0.03490 0.03031 -0.1005 0.9143 0.0552
-2.000 0.3018 0.02751 0.02261 -0.1001 0.8762 0.0706
-1.750 0.3341 0.02832 0.02295 -0.0989 0.8616 0.0808
-1.500 0.3556 0.02437 0.01901 -0.0990 0.8470 0.0835
-1.250 0.3854 0.02465 0.01883 -0.0979 0.8304 0.0948
-1.000 0.4076 0.02149 0.01570 -0.0978 0.8133 0.0986
-0.750 0.4364 0.02103 0.01484 -0.0969 0.7926 0.1087
0.250 0.5489 0.01604 0.00870 -0.0942 0.7164 0.0784
0.750 0.6042 0.01421 0.00625 -0.0928 0.6797 0.0678
1.000 0.6307 0.01353 0.00541 -0.0922 0.6612 0.0684
1.250 0.6568 0.01326 0.00504 -0.0918 0.6432 0.0726
1.500 0.6831 0.01305 0.00472 -0.0913 0.6263 0.0763
1.750 0.7094 0.01279 0.00437 -0.0908 0.6109 0.0788
2.000 0.7358 0.01257 0.00412 -0.0904 0.5973 0.0839
2.250 0.7624 0.01248 0.00401 -0.0901 0.5840 0.0997
2.500 0.7889 0.01237 0.00387 -0.0898 0.5708 0.1482
2.750 0.8146 0.01204 0.00392 -0.0897 0.5573 0.3600
3.000 0.8396 0.01105 0.00397 -0.0889 0.5435 1.0000
3.250 0.8657 0.01127 0.00406 -0.0885 0.5284 1.0000
3.500 0.8915 0.01149 0.00419 -0.0881 0.5118 1.0000
3.750 0.9173 0.01169 0.00432 -0.0877 0.4936 1.0000
4.000 0.9428 0.01191 0.00446 -0.0873 0.4741 1.0000
4.250 0.9682 0.01215 0.00462 -0.0868 0.4527 1.0000
4.500 0.9930 0.01241 0.00482 -0.0863 0.4271 1.0000
4.750 1.0174 0.01274 0.00502 -0.0858 0.3978 1.0000
5.000 1.0412 0.01315 0.00529 -0.0852 0.3711 1.0000
5.250 1.0648 0.01361 0.00561 -0.0846 0.3458 1.0000
5.500 1.0879 0.01411 0.00596 -0.0841 0.3212 1.0000
5.750 1.1115 0.01458 0.00639 -0.0835 0.3044 1.0000
6.000 1.1344 0.01510 0.00680 -0.0830 0.2842 1.0000
6.250 1.1575 0.01557 0.00720 -0.0824 0.2629 1.0000
6.500 1.1806 0.01605 0.00763 -0.0819 0.2457 1.0000
6.750 1.2035 0.01653 0.00809 -0.0813 0.2230 1.0000
7.000 1.2259 0.01707 0.00856 -0.0807 0.1959 1.0000
7.250 1.2465 0.01784 0.00909 -0.0798 0.1477 1.0000
7.500 1.2623 0.01921 0.01010 -0.0784 0.1060 1.0000
7.750 1.2726 0.02124 0.01171 -0.0763 0.0316 1.0000
8.000 1.2911 0.02222 0.01282 -0.0749 0.0272 1.0000
8.250 1.3088 0.02326 0.01406 -0.0735 0.0251 1.0000
8.500 1.3246 0.02446 0.01550 -0.0718 0.0239 1.0000
8.750 1.3368 0.02589 0.01719 -0.0697 0.0232 1.0000
9.000 1.3459 0.02742 0.01891 -0.0673 0.0230 1.0000
9.250 1.3520 0.02892 0.02058 -0.0646 0.0227 1.0000
9.500 1.3557 0.03047 0.02226 -0.0617 0.0220 1.0000
9.750 1.3576 0.03225 0.02415 -0.0590 0.0214 1.0000
10.000 1.3580 0.03430 0.02633 -0.0564 0.0212 1.0000
10.250 1.3589 0.03651 0.02862 -0.0540 0.0211 1.0000
10.500 1.3615 0.03876 0.03096 -0.0519 0.0212 1.0000
10.750 1.3672 0.04101 0.03327 -0.0499 0.0214 1.0000
11.000 1.3791 0.04321 0.03549 -0.0479 0.0219 1.0000
11.250 1.2373 0.03821 0.03127 -0.0358 0.0216 1.0000
11.500 1.2477 0.04097 0.03405 -0.0336 0.0220 1.0000
11.750 1.5138 0.05182 0.04456 -0.0487 0.0327 1.0000
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Polar data table (+)
Polar graphs
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