GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 394 AIRFOIL (goe394-il) Reynolds number: 200,000 Max Cl/Cd: 90.51 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe394-il-200000.txt Download as CSV file: xf-goe394-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 394 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 -0.2999 0.09837 0.09511 -0.0217 1.0000 0.0378
-7.750 -0.2910 0.09569 0.09248 -0.0235 1.0000 0.0396
-7.500 -0.2864 0.09361 0.09048 -0.0255 1.0000 0.0417
-7.250 -0.2547 0.09178 0.08865 -0.0445 0.9807 0.0434
-7.000 -0.2366 0.08575 0.08261 -0.0467 0.9731 0.0440
-6.750 -0.2195 0.08154 0.07839 -0.0454 0.9673 0.0452
-6.500 -0.1970 0.07818 0.07499 -0.0489 0.9578 0.0470
-6.250 -0.1744 0.07497 0.07174 -0.0537 0.9467 0.0497
-6.000 -0.1261 0.07118 0.06781 -0.0735 0.9329 0.0539
-5.750 -0.1209 0.06758 0.06423 -0.0689 0.9272 0.0548
-5.500 -0.1057 0.06492 0.06154 -0.0687 0.9202 0.0563
-5.250 -0.0839 0.06224 0.05881 -0.0714 0.9139 0.0589
-4.750 -0.0176 0.05505 0.05142 -0.0861 0.9006 0.0657
-4.500 -0.0016 0.05283 0.04916 -0.0852 0.8946 0.0677
-4.250 0.0251 0.05028 0.04653 -0.0881 0.8869 0.0711
-4.000 0.0816 0.04583 0.04172 -0.1008 0.8808 0.0765
-3.750 0.0974 0.04339 0.03932 -0.0997 0.8739 0.0776
-3.500 0.1181 0.04151 0.03740 -0.0995 0.8682 0.0803
-3.250 0.1786 0.03935 0.03460 -0.1091 0.8628 0.0881
-3.000 0.1997 0.03527 0.03056 -0.1100 0.8568 0.0891
-2.750 0.2227 0.03302 0.02828 -0.1101 0.8520 0.0902
-2.500 0.2494 0.03116 0.02636 -0.1109 0.8475 0.0920
-2.250 0.2961 0.02533 0.01976 -0.1158 0.8428 0.0748
-2.000 0.3243 0.02284 0.01708 -0.1165 0.8382 0.0708
-1.750 0.3593 0.01811 0.01142 -0.1179 0.8345 0.0666
-1.500 0.3879 0.01714 0.01026 -0.1181 0.8287 0.0683
-1.250 0.4157 0.01652 0.00945 -0.1178 0.8235 0.0725
-1.000 0.4440 0.01547 0.00804 -0.1174 0.8189 0.0764
-0.750 0.4715 0.01522 0.00781 -0.1172 0.8125 0.0811
-0.500 0.4990 0.01476 0.00719 -0.1167 0.8070 0.0910
-0.250 0.5262 0.01456 0.00697 -0.1163 0.8009 0.1092
0.000 0.5530 0.01449 0.00683 -0.1159 0.7940 0.1268
0.250 0.5796 0.01424 0.00657 -0.1154 0.7880 0.1376
0.500 0.6065 0.01404 0.00635 -0.1151 0.7801 0.1456
0.750 0.6330 0.01406 0.00631 -0.1144 0.7735 0.1569
1.000 0.6596 0.01381 0.00616 -0.1141 0.7647 0.1650
1.250 0.6863 0.01365 0.00595 -0.1134 0.7571 0.1679
1.500 0.7130 0.01350 0.00580 -0.1128 0.7476 0.1701
1.750 0.7396 0.01339 0.00568 -0.1122 0.7383 0.1722
2.000 0.7661 0.01318 0.00550 -0.1115 0.7292 0.1756
2.250 0.7925 0.01305 0.00546 -0.1110 0.7176 0.1810
2.500 0.8190 0.01295 0.00539 -0.1103 0.7059 0.1864
2.750 0.8455 0.01279 0.00531 -0.1097 0.6936 0.1924
3.000 0.8722 0.01266 0.00521 -0.1091 0.6799 0.2019
3.250 0.8985 0.01245 0.00511 -0.1085 0.6631 0.2214
3.500 0.9255 0.01103 0.00503 -0.1080 0.6436 1.0000
3.750 0.9519 0.01098 0.00489 -0.1073 0.6208 1.0000
4.000 0.9780 0.01098 0.00477 -0.1066 0.5953 1.0000
4.250 1.0038 0.01111 0.00474 -0.1059 0.5699 1.0000
4.500 1.0291 0.01137 0.00483 -0.1052 0.5482 1.0000
4.750 1.0542 0.01172 0.00505 -0.1046 0.5272 1.0000
5.000 1.0793 0.01213 0.00533 -0.1040 0.5092 1.0000
5.250 1.1043 0.01257 0.00566 -0.1034 0.4922 1.0000
5.500 1.1294 0.01297 0.00604 -0.1029 0.4767 1.0000
5.750 1.1546 0.01335 0.00642 -0.1024 0.4628 1.0000
6.000 1.1798 0.01371 0.00681 -0.1019 0.4491 1.0000
6.250 1.2047 0.01408 0.00721 -0.1014 0.4349 1.0000
6.500 1.2291 0.01444 0.00761 -0.1007 0.4191 1.0000
6.750 1.2521 0.01477 0.00795 -0.0999 0.3939 1.0000
7.000 1.2743 0.01514 0.00827 -0.0990 0.3618 1.0000
7.250 1.2965 0.01557 0.00868 -0.0982 0.3303 1.0000
7.500 1.3173 0.01617 0.00919 -0.0972 0.2874 1.0000
7.750 1.3338 0.01725 0.00992 -0.0958 0.2204 1.0000
8.000 1.3470 0.01876 0.01101 -0.0941 0.1574 1.0000
8.250 1.3605 0.02024 0.01225 -0.0925 0.1190 1.0000
8.500 1.3701 0.02213 0.01379 -0.0903 0.0688 1.0000
8.750 1.3784 0.02400 0.01546 -0.0878 0.0494 1.0000
9.000 1.3904 0.02537 0.01693 -0.0856 0.0433 1.0000
9.250 1.3943 0.02733 0.01889 -0.0827 0.0393 1.0000
9.500 1.4038 0.02857 0.02027 -0.0803 0.0367 1.0000
9.750 1.4104 0.03006 0.02184 -0.0778 0.0344 1.0000
10.000 1.4149 0.03182 0.02366 -0.0753 0.0328 1.0000
10.250 1.4172 0.03405 0.02592 -0.0726 0.0315 1.0000
10.500 1.4238 0.03637 0.02831 -0.0702 0.0304 1.0000
10.750 1.4349 0.03805 0.03015 -0.0684 0.0296 1.0000
11.000 1.4455 0.03981 0.03206 -0.0667 0.0284 1.0000
11.250 1.4552 0.04164 0.03400 -0.0650 0.0271 1.0000
11.500 1.4647 0.04362 0.03611 -0.0634 0.0261 1.0000
11.750 1.4747 0.04583 0.03844 -0.0617 0.0254 1.0000
12.000 1.4850 0.04829 0.04102 -0.0602 0.0248 1.0000
12.250 1.4953 0.05125 0.04415 -0.0586 0.0243 1.0000
12.500 1.5017 0.05475 0.04791 -0.0570 0.0241 1.0000
12.750 1.5020 0.05844 0.05186 -0.0553 0.0240 1.0000
13.000 1.4971 0.06239 0.05609 -0.0536 0.0239 1.0000
13.250 1.4879 0.06660 0.06057 -0.0523 0.0238 1.0000
13.500 1.4750 0.07112 0.06535 -0.0513 0.0237 1.0000
13.750 1.4595 0.07588 0.07038 -0.0508 0.0237 1.0000
14.000 1.4426 0.08081 0.07554 -0.0508 0.0237 1.0000
14.250 1.4253 0.08587 0.08083 -0.0513 0.0237 1.0000
14.500 1.4073 0.09117 0.08635 -0.0525 0.0237 1.0000
14.750 1.3890 0.09677 0.09216 -0.0542 0.0237 1.0000
15.000 1.3703 0.10272 0.09831 -0.0567 0.0238 1.0000
15.250 1.3523 0.10907 0.10486 -0.0601 0.0239 1.0000
15.500 1.3332 0.11629 0.11229 -0.0645 0.0241 1.0000
15.750 1.0612 0.12182 0.11844 -0.0533 0.0274 1.0000
16.000 1.0228 0.13153 0.12834 -0.0594 0.0281 1.0000
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Polar data table (+)
Polar graphs
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