GOE 514 AIRFOIL (goe514-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 514 AIRFOIL (goe514-il) Reynolds number: 500,000 Max Cl/Cd: 64.73 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe514-il-500000-n5.txt Download as CSV file: xf-goe514-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 514 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.3417 0.11147 0.10848 -0.0975 0.9765 0.0108
-16.250 -0.3562 0.10419 0.10109 -0.1019 0.9754 0.0110
-16.000 -0.3661 0.09790 0.09472 -0.1059 0.9744 0.0111
-15.750 -0.3702 0.09272 0.08947 -0.1096 0.9736 0.0111
-15.500 -0.3772 0.08709 0.08376 -0.1136 0.9728 0.0113
-15.250 -0.3834 0.08307 0.07970 -0.1153 0.9696 0.0112
-15.000 -0.3929 0.07800 0.07456 -0.1184 0.9671 0.0114
-14.750 -0.3996 0.07292 0.06939 -0.1221 0.9650 0.0116
-14.500 -0.4049 0.06799 0.06440 -0.1261 0.9632 0.0117
-14.250 -0.4138 0.06217 0.05849 -0.1312 0.9615 0.0118
-14.000 -0.4218 0.05649 0.05273 -0.1370 0.9598 0.0117
-13.750 -0.4586 0.04917 0.04533 -0.1421 0.9520 0.0118
-13.500 -0.5202 0.03632 0.03214 -0.1558 0.9458 0.0114
-13.250 -0.5432 0.03299 0.02864 -0.1527 0.9370 0.0114
-13.000 -0.5361 0.02999 0.02546 -0.1534 0.9334 0.0116
-12.750 -0.5152 0.02756 0.02284 -0.1552 0.9313 0.0119
-12.500 -0.5083 0.02582 0.02096 -0.1534 0.9261 0.0120
-12.250 -0.5026 0.02432 0.01935 -0.1510 0.9213 0.0123
-12.000 -0.4885 0.02306 0.01796 -0.1498 0.9181 0.0126
-11.750 -0.4671 0.02199 0.01679 -0.1497 0.9157 0.0128
-11.500 -0.4460 0.02102 0.01571 -0.1493 0.9132 0.0132
-11.250 -0.4431 0.02050 0.01512 -0.1448 0.9078 0.0134
-11.000 -0.4281 0.01983 0.01435 -0.1428 0.9041 0.0138
-10.750 -0.4084 0.01911 0.01352 -0.1417 0.9010 0.0142
-10.500 -0.3829 0.01844 0.01275 -0.1417 0.8985 0.0146
-10.250 -0.3659 0.01790 0.01212 -0.1398 0.8945 0.0150
-10.000 -0.3564 0.01733 0.01148 -0.1363 0.8889 0.0155
-9.750 -0.3347 0.01676 0.01084 -0.1353 0.8842 0.0162
-9.500 -0.3047 0.01615 0.01012 -0.1359 0.8805 0.0170
-9.250 -0.2952 0.01584 0.00977 -0.1322 0.8736 0.0177
-9.000 -0.2753 0.01536 0.00921 -0.1306 0.8679 0.0187
-8.750 -0.2465 0.01483 0.00861 -0.1309 0.8638 0.0201
-8.500 -0.2352 0.01454 0.00827 -0.1274 0.8564 0.0213
-8.250 -0.2124 0.01411 0.00779 -0.1264 0.8499 0.0230
-8.000 -0.1919 0.01375 0.00738 -0.1248 0.8431 0.0257
-7.750 -0.1728 0.01337 0.00697 -0.1229 0.8343 0.0293
-7.500 -0.1522 0.01301 0.00660 -0.1214 0.8257 0.0356
-7.250 -0.1288 0.01266 0.00623 -0.1204 0.8150 0.0430
-7.000 -0.1082 0.01241 0.00595 -0.1188 0.8008 0.0496
-6.750 -0.0849 0.01221 0.00569 -0.1177 0.7857 0.0554
-6.500 -0.0616 0.01203 0.00541 -0.1166 0.7668 0.0603
-6.250 -0.0403 0.01196 0.00520 -0.1150 0.7493 0.0640
-6.000 -0.0206 0.01182 0.00497 -0.1132 0.7331 0.0681
-5.750 -0.0007 0.01174 0.00480 -0.1114 0.7198 0.0720
-5.500 0.0188 0.01169 0.00465 -0.1095 0.7073 0.0748
-5.250 0.0379 0.01154 0.00445 -0.1076 0.6966 0.0798
-5.000 0.0566 0.01144 0.00429 -0.1056 0.6863 0.0842
-4.750 0.0743 0.01128 0.00412 -0.1034 0.6766 0.0930
-4.500 0.0906 0.01116 0.00402 -0.1009 0.6660 0.1056
-4.250 0.1078 0.01109 0.00400 -0.0985 0.6555 0.1261
-4.000 0.1241 0.01110 0.00394 -0.0960 0.6448 0.1349
-3.750 0.1415 0.01108 0.00388 -0.0936 0.6337 0.1408
-3.500 0.1585 0.01109 0.00383 -0.0912 0.6233 0.1456
-3.250 0.1742 0.01114 0.00379 -0.0885 0.6114 0.1495
-3.000 0.1912 0.01117 0.00374 -0.0861 0.5986 0.1520
-2.750 0.2059 0.01120 0.00372 -0.0833 0.5835 0.1564
-2.500 0.2198 0.01127 0.00372 -0.0803 0.5666 0.1596
-2.250 0.2333 0.01138 0.00373 -0.0772 0.5478 0.1624
-2.000 0.2464 0.01152 0.00375 -0.0741 0.5274 0.1645
-1.750 0.2590 0.01168 0.00379 -0.0709 0.5056 0.1663
-1.500 0.2723 0.01186 0.00384 -0.0679 0.4845 0.1677
-1.250 0.2869 0.01202 0.00390 -0.0652 0.4670 0.1704
-1.000 0.3018 0.01217 0.00396 -0.0626 0.4518 0.1728
-0.500 0.3359 0.01240 0.00410 -0.0583 0.4300 0.1804
-0.250 0.3533 0.01254 0.00417 -0.0562 0.4214 0.1830
0.000 0.3730 0.01263 0.00422 -0.0546 0.4149 0.1857
0.250 0.3914 0.01273 0.00430 -0.0527 0.4084 0.1893
0.500 0.4098 0.01284 0.00439 -0.0509 0.4030 0.1946
0.750 0.4300 0.01291 0.00447 -0.0494 0.3980 0.2015
1.000 0.4493 0.01301 0.00458 -0.0478 0.3926 0.2099
1.250 0.4676 0.01316 0.00470 -0.0460 0.3877 0.2191
1.500 0.4873 0.01326 0.00483 -0.0445 0.3831 0.2310
1.750 0.5074 0.01337 0.00495 -0.0430 0.3786 0.2412
2.000 0.5272 0.01351 0.00508 -0.0415 0.3743 0.2504
2.250 0.5460 0.01366 0.00523 -0.0399 0.3705 0.2581
2.500 0.5661 0.01381 0.00537 -0.0385 0.3672 0.2649
2.750 0.5866 0.01393 0.00551 -0.0372 0.3639 0.2715
3.000 0.6067 0.01408 0.00565 -0.0359 0.3601 0.2775
3.250 0.6262 0.01426 0.00581 -0.0345 0.3564 0.2827
3.500 0.6448 0.01444 0.00599 -0.0329 0.3527 0.2884
3.750 0.6647 0.01461 0.00617 -0.0316 0.3495 0.2936
4.000 0.6852 0.01476 0.00633 -0.0304 0.3465 0.2981
4.250 0.7050 0.01493 0.00651 -0.0291 0.3435 0.3023
4.500 0.7244 0.01512 0.00671 -0.0278 0.3404 0.3068
4.750 0.7435 0.01533 0.00691 -0.0264 0.3376 0.3120
5.000 0.7618 0.01558 0.00714 -0.0249 0.3346 0.3164
5.250 0.7818 0.01575 0.00736 -0.0238 0.3324 0.3222
5.500 0.8020 0.01594 0.00758 -0.0226 0.3296 0.3289
5.750 0.8218 0.01615 0.00781 -0.0215 0.3266 0.3339
6.000 0.8408 0.01638 0.00806 -0.0202 0.3236 0.3396
6.250 0.8594 0.01663 0.00833 -0.0189 0.3211 0.3461
6.500 0.8769 0.01692 0.00864 -0.0175 0.3184 0.3578
6.750 0.8963 0.01716 0.00892 -0.0164 0.3163 0.3680
7.000 0.9162 0.01736 0.00920 -0.0154 0.3131 0.3840
7.250 0.9360 0.01757 0.00949 -0.0144 0.3112 0.4071
7.750 1.1858 0.01832 0.01163 -0.0586 0.2981 1.0000
8.000 1.2025 0.01863 0.01196 -0.0571 0.2957 1.0000
8.250 1.2185 0.01898 0.01234 -0.0554 0.2934 1.0000
8.500 1.2335 0.01938 0.01273 -0.0537 0.2903 1.0000
8.750 1.2483 0.01981 0.01316 -0.0520 0.2876 1.0000
9.000 1.2623 0.02030 0.01365 -0.0502 0.2848 1.0000
9.250 1.2793 0.02066 0.01405 -0.0489 0.2828 1.0000
9.500 1.2960 0.02106 0.01448 -0.0476 0.2805 1.0000
9.750 1.3123 0.02148 0.01494 -0.0463 0.2784 1.0000
10.000 1.3271 0.02199 0.01547 -0.0448 0.2755 1.0000
10.250 1.3407 0.02256 0.01605 -0.0431 0.2722 1.0000
10.500 1.3537 0.02319 0.01667 -0.0415 0.2688 1.0000
10.750 1.3693 0.02370 0.01723 -0.0403 0.2638 1.0000
11.000 1.3830 0.02432 0.01788 -0.0388 0.2595 1.0000
11.250 1.3933 0.02515 0.01869 -0.0371 0.2545 1.0000
11.500 1.4076 0.02579 0.01936 -0.0358 0.2497 1.0000
11.750 1.4215 0.02646 0.02008 -0.0346 0.2459 1.0000
12.000 1.4319 0.02737 0.02100 -0.0330 0.2410 1.0000
12.250 1.4433 0.02825 0.02190 -0.0316 0.2355 1.0000
12.500 1.4540 0.02920 0.02287 -0.0302 0.2291 1.0000
12.750 1.4615 0.03038 0.02405 -0.0286 0.2222 1.0000
13.000 1.4711 0.03147 0.02516 -0.0273 0.2147 1.0000
13.250 1.4735 0.03311 0.02677 -0.0255 0.2024 1.0000
13.500 1.4762 0.03480 0.02843 -0.0238 0.1923 1.0000
13.750 1.4748 0.03687 0.03046 -0.0220 0.1788 1.0000
14.000 1.4747 0.03890 0.03248 -0.0204 0.1690 1.0000
14.250 1.4645 0.04186 0.03538 -0.0184 0.1521 1.0000
14.500 1.4584 0.04459 0.03810 -0.0168 0.1421 1.0000
14.750 1.4473 0.04789 0.04138 -0.0153 0.1301 1.0000
15.000 1.4404 0.05089 0.04441 -0.0141 0.1220 1.0000
15.250 1.4321 0.05416 0.04771 -0.0131 0.1161 1.0000
15.500 1.4255 0.05736 0.05095 -0.0124 0.1098 1.0000
15.750 1.4114 0.06147 0.05509 -0.0116 0.1033 1.0000
16.000 1.4033 0.06504 0.05873 -0.0113 0.0970 1.0000
16.250 1.3854 0.06989 0.06361 -0.0110 0.0883 1.0000
16.500 1.3583 0.07602 0.06974 -0.0110 0.0725 1.0000
16.750 1.3326 0.08217 0.07591 -0.0113 0.0621 1.0000
17.000 1.3075 0.08841 0.08218 -0.0119 0.0527 1.0000
17.250 1.2809 0.09498 0.08881 -0.0127 0.0428 1.0000
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Polar data table (+)
Polar graphs
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