GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 200,000 Max Cl/Cd: 71.87 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe387-il-200000.txt Download as CSV file: xf-goe387-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2203 0.14089 0.13705 -0.0449 1.0000 0.0477
-12.750 -0.2206 0.13836 0.13455 -0.0458 1.0000 0.0490
-12.500 -0.2442 0.13668 0.13295 -0.0496 1.0000 0.0498
-12.250 -0.2339 0.13334 0.12966 -0.0480 1.0000 0.0501
-12.000 -0.2242 0.13080 0.12716 -0.0461 1.0000 0.0505
-11.750 -0.2232 0.12919 0.12563 -0.0439 1.0000 0.0510
-11.500 -0.2332 0.12873 0.12526 -0.0406 0.9996 0.0514
-11.250 -0.2120 0.12464 0.12116 -0.0451 0.9963 0.0527
-11.000 -0.1941 0.12036 0.11688 -0.0502 0.9918 0.0547
-10.750 -0.1994 0.11491 0.11143 -0.0617 0.9848 0.0568
-10.500 -0.1660 0.11112 0.10763 -0.0617 0.9821 0.0576
-10.250 -0.1432 0.10768 0.10419 -0.0643 0.9755 0.0589
-10.000 -0.1227 0.10387 0.10037 -0.0687 0.9708 0.0606
-9.750 -0.1265 0.09870 0.09519 -0.0804 0.9600 0.0641
-9.500 -0.1027 0.09399 0.09048 -0.0834 0.9563 0.0649
-9.250 -0.0750 0.09098 0.08746 -0.0847 0.9487 0.0660
-9.000 -0.0473 0.08744 0.08389 -0.0892 0.9432 0.0680
-8.500 -0.0125 0.07723 0.07361 -0.1063 0.9246 0.0740
-8.250 0.0167 0.07482 0.07116 -0.1080 0.9137 0.0760
-8.000 0.0361 0.07147 0.06775 -0.1129 0.9005 0.0795
-7.750 -0.0072 0.06482 0.06097 -0.1242 0.8739 0.0831
-7.500 0.0305 0.06397 0.06012 -0.1206 0.8680 0.0844
-7.250 0.0436 0.06248 0.05860 -0.1194 0.8565 0.0862
-7.000 0.0441 0.06038 0.05645 -0.1195 0.8443 0.0885
-6.750 0.0091 0.05414 0.04993 -0.1257 0.8302 0.0945
-6.500 0.0282 0.05282 0.04866 -0.1239 0.8219 0.0956
-6.250 0.0451 0.05139 0.04717 -0.1229 0.8150 0.0975
-6.000 0.0472 0.04895 0.04458 -0.1234 0.8050 0.1038
-5.750 0.0509 0.04541 0.04084 -0.1236 0.7982 0.1081
-5.500 0.0666 0.04412 0.03958 -0.1222 0.7903 0.1102
-5.250 0.0695 0.04146 0.03648 -0.1220 0.7828 0.1209
-5.000 0.0904 0.03968 0.03477 -0.1212 0.7769 0.1229
-4.750 0.1071 0.03838 0.03347 -0.1200 0.7692 0.1263
-4.500 0.0986 0.02692 0.02012 -0.1159 0.7640 0.0742
-4.250 0.1213 0.02518 0.01816 -0.1148 0.7584 0.0702
-4.000 0.1403 0.02359 0.01588 -0.1122 0.7511 0.0642
-3.750 0.1654 0.02189 0.01404 -0.1116 0.7451 0.0629
-3.500 0.1896 0.02080 0.01278 -0.1107 0.7387 0.0619
-3.250 0.2135 0.01991 0.01173 -0.1096 0.7316 0.0611
-3.000 0.2411 0.01909 0.01071 -0.1091 0.7259 0.0608
-2.750 0.2658 0.01849 0.01004 -0.1082 0.7197 0.0608
-2.500 0.2908 0.01794 0.00943 -0.1073 0.7131 0.0610
-2.250 0.3184 0.01743 0.00884 -0.1069 0.7079 0.0620
-2.000 0.3427 0.01712 0.00849 -0.1060 0.7017 0.0635
-1.750 0.3668 0.01672 0.00809 -0.1050 0.6951 0.0647
-1.500 0.3929 0.01623 0.00759 -0.1044 0.6897 0.0660
-1.250 0.4157 0.01597 0.00737 -0.1033 0.6834 0.0677
-1.000 0.4397 0.01574 0.00713 -0.1023 0.6768 0.0701
-0.750 0.4670 0.01552 0.00681 -0.1018 0.6714 0.0735
-0.500 0.4897 0.01536 0.00670 -0.1006 0.6645 0.0794
-0.250 0.5138 0.01507 0.00652 -0.0997 0.6576 0.1036
0.000 0.5360 0.01427 0.00644 -0.0987 0.6522 0.3190
0.250 0.5488 0.01364 0.00658 -0.0957 0.6447 0.5112
0.500 0.7047 0.01264 0.00643 -0.1214 0.6356 1.0000
0.750 0.7252 0.01277 0.00648 -0.1199 0.6279 1.0000
1.000 0.7480 0.01284 0.00642 -0.1187 0.6205 1.0000
1.250 0.7711 0.01295 0.00641 -0.1176 0.6132 1.0000
1.500 0.7922 0.01304 0.00643 -0.1162 0.6045 1.0000
1.750 0.8170 0.01314 0.00638 -0.1154 0.5976 1.0000
2.000 0.8365 0.01326 0.00649 -0.1137 0.5884 1.0000
2.250 0.8618 0.01337 0.00643 -0.1130 0.5813 1.0000
2.500 0.8808 0.01351 0.00658 -0.1112 0.5718 1.0000
2.750 0.9054 0.01362 0.00655 -0.1104 0.5641 1.0000
3.000 0.9243 0.01377 0.00669 -0.1086 0.5540 1.0000
3.250 0.9483 0.01389 0.00666 -0.1077 0.5456 1.0000
3.500 0.9666 0.01403 0.00680 -0.1057 0.5348 1.0000
3.750 0.9884 0.01418 0.00686 -0.1045 0.5257 1.0000
4.000 1.0085 0.01435 0.00698 -0.1029 0.5162 1.0000
4.250 1.0296 0.01456 0.00712 -0.1016 0.5073 1.0000
4.500 1.0504 0.01475 0.00726 -0.1001 0.4986 1.0000
4.750 1.0712 0.01500 0.00745 -0.0988 0.4902 1.0000
5.000 1.0919 0.01524 0.00764 -0.0974 0.4822 1.0000
5.250 1.1135 0.01552 0.00786 -0.0963 0.4748 1.0000
5.500 1.1332 0.01579 0.00811 -0.0947 0.4670 1.0000
5.750 1.1564 0.01609 0.00831 -0.0939 0.4604 1.0000
6.000 1.1742 0.01638 0.00864 -0.0921 0.4528 1.0000
6.250 1.1967 0.01668 0.00885 -0.0912 0.4463 1.0000
6.500 1.2155 0.01702 0.00920 -0.0896 0.4396 1.0000
6.750 1.2344 0.01731 0.00949 -0.0880 0.4328 1.0000
7.000 1.2579 0.01768 0.00977 -0.0873 0.4270 1.0000
7.250 1.2743 0.01802 0.01018 -0.0854 0.4210 1.0000
7.500 1.2944 0.01836 0.01052 -0.0841 0.4156 1.0000
7.750 1.3192 0.01877 0.01085 -0.0837 0.4105 1.0000
8.000 1.3338 0.01913 0.01132 -0.0815 0.4051 1.0000
8.250 1.3523 0.01949 0.01170 -0.0800 0.3998 1.0000
8.500 1.3782 0.01991 0.01203 -0.0799 0.3948 1.0000
8.750 1.3904 0.02032 0.01255 -0.0773 0.3897 1.0000
9.000 1.4058 0.02071 0.01299 -0.0753 0.3843 1.0000
9.250 1.4280 0.02111 0.01335 -0.0746 0.3792 1.0000
9.500 1.4393 0.02155 0.01387 -0.0719 0.3739 1.0000
9.750 1.4477 0.02194 0.01432 -0.0687 0.3678 1.0000
10.000 1.4689 0.02233 0.01460 -0.0678 0.3612 1.0000
10.250 1.4686 0.02283 0.01525 -0.0634 0.3549 1.0000
10.500 1.4777 0.02328 0.01573 -0.0607 0.3481 1.0000
10.750 1.4898 0.02383 0.01628 -0.0586 0.3416 1.0000
11.000 1.4944 0.02447 0.01702 -0.0555 0.3350 1.0000
11.250 1.5107 0.02499 0.01747 -0.0541 0.3286 1.0000
11.500 1.5121 0.02585 0.01849 -0.0509 0.3218 1.0000
11.750 1.5192 0.02661 0.01927 -0.0486 0.3148 1.0000
12.000 1.5247 0.02753 0.02024 -0.0463 0.3074 1.0000
12.250 1.5276 0.02857 0.02135 -0.0438 0.2997 1.0000
12.500 1.5331 0.02963 0.02243 -0.0418 0.2921 1.0000
12.750 1.5346 0.03093 0.02382 -0.0396 0.2841 1.0000
13.000 1.5396 0.03217 0.02507 -0.0379 0.2767 1.0000
13.250 1.5412 0.03367 0.02666 -0.0360 0.2691 1.0000
13.500 1.5471 0.03499 0.02795 -0.0346 0.2624 1.0000
13.750 1.5480 0.03671 0.02980 -0.0330 0.2551 1.0000
14.000 1.5548 0.03804 0.03106 -0.0318 0.2490 1.0000
14.250 1.5543 0.04004 0.03323 -0.0305 0.2422 1.0000
14.500 1.5579 0.04172 0.03489 -0.0293 0.2362 1.0000
14.750 1.5588 0.04374 0.03699 -0.0283 0.2298 1.0000
15.000 1.5597 0.04580 0.03910 -0.0273 0.2236 1.0000
15.250 1.5625 0.04772 0.04102 -0.0264 0.2181 1.0000
15.500 1.5606 0.05021 0.04363 -0.0257 0.2117 1.0000
15.750 1.5637 0.05214 0.04547 -0.0249 0.2058 1.0000
16.000 1.5598 0.05501 0.04851 -0.0245 0.2000 1.0000
16.250 1.5592 0.05747 0.05096 -0.0239 0.1941 1.0000
16.500 1.5584 0.06003 0.05357 -0.0235 0.1886 1.0000
16.750 1.5544 0.06305 0.05668 -0.0232 0.1826 1.0000
17.000 1.5563 0.06526 0.05881 -0.0228 0.1767 1.0000
17.250 1.5483 0.06894 0.06266 -0.0229 0.1711 1.0000
17.500 1.5481 0.07147 0.06510 -0.0226 0.1647 1.0000
17.750 1.5393 0.07535 0.06915 -0.0229 0.1592 1.0000
18.000 1.5326 0.07899 0.07284 -0.0232 0.1534 1.0000
18.250 1.5293 0.08215 0.07603 -0.0233 0.1478 1.0000
18.500 1.5196 0.08639 0.08041 -0.0241 0.1424 1.0000
18.750 1.5190 0.08920 0.08315 -0.0243 0.1374 1.0000
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