GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 200,000 Max Cl/Cd: 74.47 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe414-il-200000.txt Download as CSV file: xf-goe414-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2157 0.08801 0.08480 -0.0733 0.9722 0.0710
-8.250 -0.2026 0.08403 0.08081 -0.0779 0.9666 0.0740
-8.000 -0.2822 0.05039 0.04675 -0.1105 0.9439 0.0457
-7.750 -0.2828 0.04300 0.03895 -0.1136 0.9348 0.0452
-7.500 -0.2699 0.03556 0.03069 -0.1172 0.9289 0.0455
-7.250 -0.2413 0.03069 0.02503 -0.1202 0.9262 0.0460
-7.000 -0.2300 0.02745 0.02138 -0.1185 0.9163 0.0471
-6.750 -0.1938 0.02619 0.02005 -0.1206 0.9133 0.0500
-6.500 -0.1665 0.02478 0.01837 -0.1208 0.9077 0.0525
-6.250 -0.1398 0.02319 0.01640 -0.1206 0.9013 0.0546
-6.000 -0.1059 0.02154 0.01455 -0.1219 0.8980 0.0577
-5.750 -0.0805 0.02091 0.01388 -0.1213 0.8903 0.0610
-5.500 -0.0492 0.01990 0.01265 -0.1217 0.8850 0.0646
-5.250 -0.0155 0.01878 0.01143 -0.1226 0.8816 0.0694
-5.000 0.0074 0.01830 0.01091 -0.1215 0.8718 0.0745
-4.750 0.0394 0.01729 0.00980 -0.1219 0.8674 0.0819
-4.500 0.0638 0.01686 0.00929 -0.1211 0.8582 0.0935
-4.250 0.0938 0.01615 0.00862 -0.1213 0.8530 0.1129
-4.000 0.1189 0.01584 0.00826 -0.1207 0.8441 0.1275
-3.750 0.1492 0.01544 0.00777 -0.1209 0.8381 0.1394
-3.500 0.1747 0.01523 0.00750 -0.1204 0.8289 0.1496
-3.250 0.2044 0.01477 0.00702 -0.1206 0.8226 0.1593
-3.000 0.2297 0.01454 0.00674 -0.1200 0.8130 0.1690
-2.750 0.2596 0.01419 0.00634 -0.1202 0.8068 0.1820
-2.500 0.2842 0.01393 0.00614 -0.1196 0.7967 0.1968
-2.250 0.3117 0.01357 0.00585 -0.1195 0.7891 0.2175
-2.000 0.3377 0.01324 0.00565 -0.1191 0.7799 0.2530
-1.750 0.3635 0.01293 0.00552 -0.1187 0.7710 0.3124
-1.500 0.3907 0.01265 0.00533 -0.1184 0.7626 0.3683
-1.250 0.4154 0.01243 0.00523 -0.1178 0.7523 0.4168
-1.000 0.4408 0.01209 0.00507 -0.1173 0.7435 0.4801
-0.750 0.4605 0.01140 0.00503 -0.1155 0.7338 0.6543
-0.500 0.5451 0.01084 0.00498 -0.1264 0.7236 1.0000
-0.250 0.5704 0.01089 0.00485 -0.1258 0.7137 1.0000
0.000 0.5951 0.01095 0.00475 -0.1252 0.7030 1.0000
0.250 0.6189 0.01104 0.00472 -0.1243 0.6915 1.0000
0.500 0.6433 0.01115 0.00469 -0.1236 0.6802 1.0000
0.750 0.6682 0.01127 0.00466 -0.1230 0.6692 1.0000
1.000 0.6928 0.01142 0.00465 -0.1223 0.6574 1.0000
1.250 0.7162 0.01158 0.00471 -0.1214 0.6446 1.0000
1.500 0.7400 0.01177 0.00479 -0.1206 0.6320 1.0000
1.750 0.7643 0.01198 0.00488 -0.1200 0.6202 1.0000
2.000 0.7894 0.01221 0.00497 -0.1194 0.6096 1.0000
2.250 0.8130 0.01242 0.00512 -0.1187 0.5983 1.0000
2.500 0.8371 0.01266 0.00529 -0.1180 0.5879 1.0000
2.750 0.8626 0.01290 0.00541 -0.1177 0.5792 1.0000
3.000 0.8859 0.01311 0.00560 -0.1169 0.5693 1.0000
3.250 0.9106 0.01334 0.00577 -0.1164 0.5609 1.0000
3.500 0.9350 0.01354 0.00593 -0.1158 0.5527 1.0000
3.750 0.9601 0.01379 0.00614 -0.1154 0.5459 1.0000
4.000 0.9847 0.01402 0.00637 -0.1150 0.5390 1.0000
4.250 1.0107 0.01427 0.00655 -0.1147 0.5333 1.0000
4.500 1.0343 0.01449 0.00682 -0.1141 0.5262 1.0000
4.750 1.0601 0.01473 0.00700 -0.1139 0.5206 1.0000
5.000 1.0842 0.01499 0.00731 -0.1133 0.5144 1.0000
5.250 1.1088 0.01523 0.00756 -0.1129 0.5086 1.0000
5.500 1.1358 0.01553 0.00781 -0.1129 0.5042 1.0000
5.750 1.1593 0.01582 0.00821 -0.1123 0.4992 1.0000
6.000 1.1845 0.01611 0.00854 -0.1121 0.4945 1.0000
6.250 1.2117 0.01642 0.00880 -0.1121 0.4897 1.0000
6.500 1.2318 0.01666 0.00916 -0.1109 0.4817 1.0000
6.750 1.2536 0.01688 0.00935 -0.1098 0.4717 1.0000
7.000 1.2741 0.01711 0.00956 -0.1086 0.4614 1.0000
7.250 1.2938 0.01739 0.00993 -0.1073 0.4525 1.0000
7.500 1.3146 0.01769 0.01021 -0.1062 0.4425 1.0000
7.750 1.3318 0.01796 0.01051 -0.1043 0.4311 1.0000
8.000 1.3480 0.01826 0.01091 -0.1024 0.4207 1.0000
8.250 1.3622 0.01857 0.01125 -0.1001 0.4081 1.0000
8.500 1.3715 0.01888 0.01160 -0.0969 0.3926 1.0000
8.750 1.3775 0.01921 0.01200 -0.0931 0.3764 1.0000
9.000 1.3803 0.01970 0.01249 -0.0889 0.3546 1.0000
9.250 1.3828 0.02038 0.01317 -0.0851 0.3202 1.0000
9.500 1.3700 0.02206 0.01446 -0.0796 0.2587 1.0000
9.750 1.3552 0.02442 0.01646 -0.0745 0.2117 1.0000
10.000 1.3375 0.02731 0.01896 -0.0698 0.1397 1.0000
10.250 1.3144 0.03089 0.02214 -0.0652 0.0866 1.0000
10.500 1.2964 0.03439 0.02538 -0.0617 0.0453 1.0000
10.750 1.2933 0.03689 0.02790 -0.0596 0.0380 1.0000
11.000 1.2933 0.03922 0.03033 -0.0579 0.0351 1.0000
11.250 1.2913 0.04184 0.03308 -0.0563 0.0332 1.0000
11.500 1.2870 0.04482 0.03621 -0.0549 0.0318 1.0000
11.750 1.2855 0.04765 0.03919 -0.0538 0.0311 1.0000
12.000 1.2829 0.05073 0.04242 -0.0529 0.0304 1.0000
12.250 1.2789 0.05406 0.04589 -0.0522 0.0297 1.0000
12.500 1.2738 0.05759 0.04955 -0.0516 0.0290 1.0000
12.750 1.2683 0.06126 0.05334 -0.0512 0.0283 1.0000
13.000 1.2625 0.06503 0.05721 -0.0509 0.0277 1.0000
13.250 1.2563 0.06888 0.06115 -0.0506 0.0270 1.0000
13.500 1.2498 0.07275 0.06508 -0.0504 0.0264 1.0000
13.750 1.2447 0.07639 0.06877 -0.0500 0.0259 1.0000
14.000 1.2425 0.07946 0.07189 -0.0492 0.0255 1.0000
14.250 1.2457 0.08143 0.07383 -0.0477 0.0250 1.0000
14.500 1.2535 0.08322 0.07568 -0.0467 0.0248 1.0000
14.750 1.2637 0.08461 0.07713 -0.0455 0.0245 1.0000
15.000 1.2767 0.08556 0.07812 -0.0440 0.0243 1.0000
15.250 1.2913 0.08636 0.07898 -0.0425 0.0241 1.0000
15.500 1.3036 0.08762 0.08033 -0.0412 0.0236 1.0000
15.750 1.3144 0.08918 0.08202 -0.0403 0.0231 1.0000
16.000 1.3250 0.09081 0.08376 -0.0393 0.0226 1.0000
16.250 1.3375 0.09228 0.08537 -0.0380 0.0226 1.0000
16.500 1.3488 0.09409 0.08735 -0.0368 0.0227 1.0000
16.750 1.3574 0.09642 0.08987 -0.0359 0.0230 1.0000
17.000 1.3632 0.09925 0.09291 -0.0352 0.0234 1.0000
17.250 1.3676 0.10244 0.09631 -0.0346 0.0239 1.0000
17.500 1.4054 0.10333 0.09729 -0.0316 0.0254 1.0000
17.750 1.3894 0.10760 0.10183 -0.0333 0.0259 1.0000
18.000 1.3498 0.11613 0.11088 -0.0372 0.0271 1.0000
18.250 1.3245 0.12429 0.11944 -0.0401 0.0292 1.0000
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