GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 500,000 Max Cl/Cd: 101.61 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe650-il-500000.txt Download as CSV file: xf-goe650-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7085 0.09198 0.08883 -0.0680 1.0000 0.0325
-15.500 -0.7585 0.08012 0.07676 -0.0753 1.0000 0.0323
-15.250 -0.7863 0.07260 0.06910 -0.0799 1.0000 0.0324
-15.000 -0.8102 0.06648 0.06286 -0.0833 1.0000 0.0324
-14.750 -0.8314 0.06103 0.05730 -0.0863 1.0000 0.0326
-14.500 -0.8506 0.05628 0.05244 -0.0886 1.0000 0.0327
-14.250 -0.8693 0.05193 0.04799 -0.0903 1.0000 0.0328
-14.000 -0.8867 0.04820 0.04418 -0.0911 1.0000 0.0329
-13.750 -0.9071 0.04465 0.04055 -0.0914 1.0000 0.0330
-13.500 -0.9311 0.04157 0.03741 -0.0906 1.0000 0.0330
-13.250 -0.9658 0.03869 0.03448 -0.0886 0.9998 0.0330
-13.000 -0.9418 0.03436 0.02987 -0.0987 0.9952 0.0333
-12.750 -0.9225 0.03128 0.02670 -0.1024 0.9915 0.0339
-12.500 -0.8984 0.02937 0.02475 -0.1052 0.9875 0.0346
-12.250 -0.8701 0.02782 0.02312 -0.1081 0.9847 0.0354
-12.000 -0.8398 0.02640 0.02159 -0.1110 0.9827 0.0361
-11.750 -0.8165 0.02515 0.02023 -0.1120 0.9783 0.0367
-11.500 -0.7894 0.02398 0.01894 -0.1134 0.9747 0.0374
-11.250 -0.7586 0.02295 0.01778 -0.1153 0.9723 0.0379
-11.000 -0.7282 0.02156 0.01631 -0.1174 0.9705 0.0388
-10.750 -0.7042 0.02048 0.01520 -0.1179 0.9662 0.0398
-10.500 -0.6770 0.01961 0.01428 -0.1186 0.9619 0.0406
-10.250 -0.6452 0.01877 0.01338 -0.1201 0.9596 0.0417
-10.000 -0.6117 0.01800 0.01252 -0.1218 0.9579 0.0426
-9.750 -0.5770 0.01731 0.01173 -0.1237 0.9567 0.0435
-9.500 -0.5522 0.01640 0.01079 -0.1238 0.9522 0.0449
-9.250 -0.5242 0.01571 0.01007 -0.1242 0.9481 0.0464
-9.000 -0.4907 0.01509 0.00940 -0.1256 0.9459 0.0481
-8.750 -0.4556 0.01451 0.00874 -0.1273 0.9442 0.0499
-8.500 -0.4213 0.01377 0.00800 -0.1290 0.9424 0.0530
-8.250 -0.3857 0.01320 0.00739 -0.1307 0.9407 0.0572
-8.000 -0.3647 0.01274 0.00694 -0.1294 0.9330 0.0635
-7.750 -0.3326 0.01218 0.00645 -0.1304 0.9295 0.0767
-7.500 -0.2981 0.01185 0.00613 -0.1317 0.9267 0.0907
-7.250 -0.2688 0.01162 0.00592 -0.1320 0.9217 0.0991
-7.000 -0.2399 0.01144 0.00569 -0.1320 0.9156 0.1053
-6.750 -0.2071 0.01123 0.00547 -0.1328 0.9110 0.1113
-6.500 -0.1771 0.01115 0.00530 -0.1330 0.9050 0.1155
-6.250 -0.1501 0.01088 0.00505 -0.1327 0.8978 0.1208
-6.000 -0.1178 0.01074 0.00485 -0.1334 0.8927 0.1255
-5.750 -0.0917 0.01067 0.00472 -0.1328 0.8855 0.1287
-5.500 -0.0643 0.01041 0.00446 -0.1326 0.8791 0.1338
-5.250 -0.0344 0.01030 0.00431 -0.1328 0.8733 0.1387
-5.000 -0.0085 0.01023 0.00419 -0.1322 0.8655 0.1427
-4.750 0.0199 0.01001 0.00396 -0.1321 0.8597 0.1487
-4.500 0.0471 0.00990 0.00384 -0.1318 0.8538 0.1536
-4.250 0.0741 0.00983 0.00372 -0.1314 0.8475 0.1580
-4.000 0.1022 0.00963 0.00351 -0.1313 0.8422 0.1647
-3.750 0.1293 0.00955 0.00342 -0.1309 0.8364 0.1711
-3.500 0.1558 0.00942 0.00329 -0.1305 0.8305 0.1777
-3.250 0.1839 0.00929 0.00316 -0.1303 0.8255 0.1850
-3.000 0.2117 0.00923 0.00306 -0.1301 0.8203 0.1918
-2.750 0.2376 0.00908 0.00297 -0.1295 0.8142 0.2009
-2.500 0.2655 0.00898 0.00284 -0.1293 0.8080 0.2107
-2.250 0.2920 0.00889 0.00278 -0.1288 0.8011 0.2230
-2.000 0.3182 0.00877 0.00270 -0.1282 0.7936 0.2377
-1.750 0.3459 0.00870 0.00263 -0.1279 0.7867 0.2544
-1.500 0.3713 0.00861 0.00260 -0.1271 0.7788 0.2723
-1.250 0.3993 0.00857 0.00255 -0.1269 0.7714 0.2915
-1.000 0.4243 0.00851 0.00255 -0.1261 0.7630 0.3091
-0.750 0.4516 0.00849 0.00253 -0.1257 0.7553 0.3257
-0.500 0.4776 0.00847 0.00255 -0.1250 0.7480 0.3408
-0.250 0.5041 0.00846 0.00255 -0.1245 0.7403 0.3556
0.000 0.5308 0.00847 0.00256 -0.1240 0.7326 0.3692
0.250 0.5567 0.00847 0.00257 -0.1233 0.7240 0.3822
0.500 0.5830 0.00848 0.00259 -0.1227 0.7157 0.3954
0.750 0.6084 0.00848 0.00261 -0.1219 0.7062 0.4078
1.000 0.6343 0.00850 0.00264 -0.1213 0.6968 0.4203
1.250 0.6593 0.00851 0.00266 -0.1204 0.6860 0.4332
1.500 0.6841 0.00851 0.00270 -0.1195 0.6743 0.4456
1.750 0.7087 0.00855 0.00272 -0.1186 0.6618 0.4582
2.000 0.7324 0.00858 0.00276 -0.1175 0.6468 0.4720
2.250 0.7555 0.00861 0.00280 -0.1162 0.6296 0.4863
2.500 0.7778 0.00868 0.00285 -0.1149 0.6091 0.5010
2.750 0.7988 0.00879 0.00293 -0.1132 0.5857 0.5176
3.000 0.8188 0.00895 0.00303 -0.1114 0.5634 0.5374
3.250 0.8387 0.00911 0.00317 -0.1096 0.5407 0.5621
3.500 0.8583 0.00927 0.00334 -0.1078 0.5200 0.5925
3.750 0.8773 0.00942 0.00351 -0.1059 0.4999 0.6293
4.000 0.8952 0.00951 0.00369 -0.1037 0.4803 0.6858
4.250 0.9541 0.00939 0.00404 -0.1106 0.4479 1.0000
4.500 0.9725 0.00971 0.00421 -0.1086 0.4223 1.0000
4.750 0.9892 0.01008 0.00442 -0.1063 0.3923 1.0000
5.000 1.0061 0.01046 0.00466 -0.1041 0.3656 1.0000
5.250 1.0224 0.01086 0.00492 -0.1018 0.3440 1.0000
5.500 1.0389 0.01121 0.00517 -0.0995 0.3275 1.0000
5.750 1.0562 0.01154 0.00543 -0.0973 0.3138 1.0000
6.000 1.0735 0.01188 0.00570 -0.0952 0.3015 1.0000
6.500 1.1092 0.01255 0.00626 -0.0913 0.2779 1.0000
6.750 1.1274 0.01289 0.00656 -0.0895 0.2669 1.0000
7.250 1.1638 0.01359 0.00717 -0.0859 0.2457 1.0000
7.500 1.1815 0.01397 0.00750 -0.0841 0.2367 1.0000
7.750 1.2000 0.01432 0.00784 -0.0825 0.2278 1.0000
8.000 1.2178 0.01471 0.00820 -0.0807 0.2195 1.0000
8.250 1.2351 0.01513 0.00859 -0.0790 0.2100 1.0000
8.500 1.2530 0.01553 0.00898 -0.0773 0.2016 1.0000
8.750 1.2692 0.01602 0.00942 -0.0755 0.1932 1.0000
9.000 1.2871 0.01644 0.00985 -0.0739 0.1859 1.0000
9.250 1.3028 0.01697 0.01035 -0.0721 0.1783 1.0000
9.500 1.3200 0.01744 0.01083 -0.0705 0.1714 1.0000
9.750 1.3354 0.01801 0.01138 -0.0687 0.1642 1.0000
10.000 1.3516 0.01856 0.01192 -0.0671 0.1576 1.0000
10.250 1.3668 0.01916 0.01251 -0.0654 0.1508 1.0000
10.500 1.3816 0.01981 0.01316 -0.0637 0.1453 1.0000
10.750 1.3978 0.02038 0.01377 -0.0622 0.1404 1.0000
11.000 1.4109 0.02115 0.01451 -0.0604 0.1349 1.0000
11.250 1.4264 0.02180 0.01519 -0.0589 0.1303 1.0000
11.500 1.4409 0.02252 0.01593 -0.0574 0.1249 1.0000
11.750 1.4528 0.02341 0.01681 -0.0557 0.1200 1.0000
12.000 1.4685 0.02409 0.01755 -0.0544 0.1155 1.0000
12.250 1.4804 0.02502 0.01847 -0.0528 0.1099 1.0000
12.500 1.4935 0.02590 0.01937 -0.0514 0.1034 1.0000
12.750 1.5032 0.02703 0.02048 -0.0497 0.0965 1.0000
13.000 1.5146 0.02808 0.02154 -0.0483 0.0881 1.0000
13.250 1.5211 0.02951 0.02291 -0.0465 0.0762 1.0000
13.500 1.5234 0.03132 0.02462 -0.0446 0.0593 1.0000
13.750 1.5220 0.03348 0.02669 -0.0426 0.0472 1.0000
14.000 1.5233 0.03550 0.02871 -0.0409 0.0427 1.0000
14.250 1.5239 0.03765 0.03089 -0.0394 0.0399 1.0000
14.500 1.5266 0.03969 0.03300 -0.0381 0.0384 1.0000
14.750 1.5290 0.04181 0.03519 -0.0370 0.0371 1.0000
15.000 1.5294 0.04420 0.03767 -0.0359 0.0361 1.0000
15.250 1.5260 0.04707 0.04060 -0.0350 0.0349 1.0000
15.500 1.5208 0.05022 0.04384 -0.0342 0.0341 1.0000
15.750 1.5199 0.05303 0.04675 -0.0337 0.0334 1.0000
16.000 1.5184 0.05599 0.04982 -0.0334 0.0326 1.0000
16.250 1.5152 0.05927 0.05320 -0.0332 0.0321 1.0000
16.500 1.5099 0.06289 0.05692 -0.0333 0.0316 1.0000
16.750 1.5030 0.06684 0.06098 -0.0336 0.0310 1.0000
17.000 1.4933 0.07128 0.06551 -0.0342 0.0306 1.0000
17.250 1.4824 0.07598 0.07031 -0.0351 0.0302 1.0000
17.500 1.4682 0.08123 0.07566 -0.0362 0.0297 1.0000
17.750 1.4534 0.08668 0.08120 -0.0375 0.0294 1.0000
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Polar data table (+)
Polar graphs
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