GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 502 AIRFOIL (goe502-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.71 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe502-il-1000000-n5.txt Download as CSV file: xf-goe502-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 502 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6427 0.09238 0.08957 -0.0947 0.9945 0.0282
-16.750 -0.6543 0.08611 0.08321 -0.0996 0.9925 0.0284
-16.500 -0.6604 0.08117 0.07819 -0.1032 0.9906 0.0285
-16.250 -0.6661 0.07617 0.07310 -0.1072 0.9882 0.0286
-16.000 -0.6704 0.07126 0.06811 -0.1114 0.9856 0.0287
-15.750 -0.6687 0.06715 0.06394 -0.1153 0.9830 0.0288
-15.500 -0.6716 0.06271 0.05942 -0.1192 0.9792 0.0289
-15.250 -0.6768 0.05862 0.05528 -0.1223 0.9729 0.0291
-14.750 -0.6793 0.04990 0.04643 -0.1316 0.9610 0.0293
-14.500 -0.6748 0.04509 0.04153 -0.1386 0.9547 0.0294
-14.250 -0.6681 0.04020 0.03654 -0.1463 0.9455 0.0296
-14.000 -0.6488 0.03530 0.03152 -0.1564 0.9386 0.0298
-13.750 -0.6316 0.03008 0.02615 -0.1671 0.9287 0.0299
-13.500 -0.6314 0.02475 0.02062 -0.1752 0.9144 0.0301
-13.250 -0.6207 0.02121 0.01686 -0.1805 0.9045 0.0302
-13.000 -0.6081 0.02006 0.01562 -0.1804 0.8975 0.0304
-12.750 -0.5908 0.01921 0.01468 -0.1803 0.8912 0.0306
-12.500 -0.5723 0.01844 0.01384 -0.1800 0.8860 0.0308
-12.250 -0.5532 0.01782 0.01316 -0.1795 0.8810 0.0311
-12.000 -0.5328 0.01724 0.01251 -0.1790 0.8754 0.0314
-11.750 -0.5114 0.01669 0.01187 -0.1786 0.8690 0.0316
-11.500 -0.4901 0.01618 0.01131 -0.1781 0.8624 0.0319
-11.250 -0.4683 0.01570 0.01074 -0.1775 0.8534 0.0321
-11.000 -0.4457 0.01527 0.01024 -0.1770 0.8442 0.0323
-10.750 -0.4230 0.01488 0.00976 -0.1763 0.8331 0.0325
-10.500 -0.4001 0.01450 0.00929 -0.1757 0.8195 0.0327
-10.250 -0.3789 0.01407 0.00875 -0.1748 0.8002 0.0330
-10.000 -0.3578 0.01375 0.00831 -0.1738 0.7785 0.0333
-9.750 -0.3352 0.01348 0.00793 -0.1729 0.7616 0.0336
-9.500 -0.3113 0.01322 0.00759 -0.1723 0.7498 0.0339
-9.250 -0.2873 0.01299 0.00728 -0.1717 0.7395 0.0343
-9.000 -0.2617 0.01274 0.00698 -0.1713 0.7326 0.0346
-8.750 -0.2363 0.01251 0.00670 -0.1709 0.7259 0.0350
-8.500 -0.2109 0.01230 0.00641 -0.1705 0.7198 0.0354
-8.250 -0.1845 0.01206 0.00613 -0.1702 0.7147 0.0358
-8.000 -0.1582 0.01185 0.00587 -0.1699 0.7094 0.0362
-7.750 -0.1319 0.01167 0.00564 -0.1696 0.7045 0.0366
-7.500 -0.1059 0.01146 0.00538 -0.1692 0.7001 0.0370
-7.250 -0.0789 0.01121 0.00511 -0.1690 0.6968 0.0376
-7.000 -0.0518 0.01101 0.00490 -0.1688 0.6926 0.0381
-6.750 -0.0249 0.01084 0.00470 -0.1686 0.6879 0.0386
-6.500 0.0017 0.01070 0.00452 -0.1682 0.6832 0.0392
-6.250 0.0286 0.01056 0.00434 -0.1679 0.6792 0.0397
-6.000 0.0563 0.01040 0.00416 -0.1678 0.6758 0.0403
-5.750 0.0838 0.01025 0.00399 -0.1676 0.6714 0.0408
-5.500 0.1108 0.01013 0.00383 -0.1673 0.6663 0.0413
-5.250 0.1372 0.00998 0.00364 -0.1669 0.6611 0.0420
-5.000 0.1647 0.00984 0.00349 -0.1667 0.6571 0.0429
-4.750 0.1923 0.00972 0.00336 -0.1665 0.6523 0.0437
-4.500 0.2194 0.00962 0.00324 -0.1662 0.6463 0.0446
-4.250 0.2458 0.00955 0.00312 -0.1658 0.6400 0.0453
-4.000 0.2735 0.00946 0.00301 -0.1656 0.6342 0.0459
-3.750 0.3002 0.00934 0.00287 -0.1652 0.6270 0.0470
-3.500 0.3265 0.00927 0.00276 -0.1647 0.6195 0.0480
-3.250 0.3533 0.00919 0.00266 -0.1644 0.6105 0.0491
-3.000 0.3791 0.00917 0.00258 -0.1638 0.6008 0.0502
-2.750 0.4055 0.00914 0.00251 -0.1633 0.5905 0.0512
-2.500 0.4309 0.00909 0.00242 -0.1627 0.5798 0.0529
-2.250 0.4563 0.00908 0.00236 -0.1620 0.5684 0.0545
-2.000 0.4820 0.00908 0.00231 -0.1614 0.5584 0.0564
-1.750 0.5072 0.00908 0.00227 -0.1607 0.5488 0.0595
-1.500 0.5329 0.00898 0.00220 -0.1602 0.5407 0.0727
-1.250 0.5577 0.00886 0.00216 -0.1595 0.5322 0.1115
-1.000 0.5834 0.00884 0.00216 -0.1590 0.5255 0.1248
-0.750 0.6093 0.00881 0.00216 -0.1584 0.5189 0.1388
-0.500 0.6344 0.00883 0.00218 -0.1578 0.5124 0.1519
-0.250 0.6602 0.00882 0.00220 -0.1572 0.5071 0.1665
0.000 0.6861 0.00881 0.00223 -0.1567 0.5018 0.1815
0.250 0.7115 0.00883 0.00227 -0.1561 0.4966 0.1952
0.500 0.7361 0.00888 0.00232 -0.1553 0.4912 0.2075
0.750 0.7623 0.00888 0.00237 -0.1548 0.4872 0.2201
1.000 0.7879 0.00891 0.00242 -0.1542 0.4826 0.2329
1.250 0.8129 0.00895 0.00248 -0.1535 0.4782 0.2436
1.500 0.8366 0.00903 0.00255 -0.1525 0.4734 0.2511
1.750 0.8609 0.00906 0.00261 -0.1517 0.4696 0.2619
2.000 0.8853 0.00910 0.00267 -0.1508 0.4653 0.2698
2.250 0.9090 0.00916 0.00274 -0.1498 0.4611 0.2778
2.500 0.9315 0.00924 0.00283 -0.1487 0.4560 0.2887
2.750 0.9547 0.00931 0.00292 -0.1476 0.4510 0.2995
3.000 0.9784 0.00938 0.00300 -0.1467 0.4450 0.3109
3.250 1.0004 0.00949 0.00312 -0.1454 0.4384 0.3217
3.500 1.0228 0.00961 0.00324 -0.1442 0.4334 0.3308
3.750 1.0465 0.00969 0.00336 -0.1433 0.4287 0.3410
4.000 1.0689 0.00981 0.00349 -0.1422 0.4224 0.3522
4.250 1.0900 0.00998 0.00365 -0.1408 0.4160 0.3636
4.750 1.1347 0.01022 0.00394 -0.1385 0.4038 0.3931
5.000 1.1552 0.01039 0.00413 -0.1371 0.3982 0.4086
5.250 1.1780 0.01050 0.00428 -0.1360 0.3939 0.4243
5.500 1.1994 0.01065 0.00446 -0.1348 0.3875 0.4415
5.750 1.2186 0.01087 0.00468 -0.1331 0.3801 0.4584
6.000 1.2397 0.01102 0.00487 -0.1319 0.3737 0.4753
6.250 1.2586 0.01125 0.00511 -0.1302 0.3656 0.4927
6.500 1.2785 0.01144 0.00534 -0.1288 0.3590 0.5146
6.750 1.2966 0.01165 0.00561 -0.1270 0.3504 0.5521
7.000 1.3121 0.01173 0.00598 -0.1249 0.3415 0.6970
7.500 1.3615 0.01208 0.00673 -0.1245 0.3165 1.0000
7.750 1.3782 0.01249 0.00709 -0.1227 0.3060 1.0000
8.000 1.3940 0.01295 0.00750 -0.1208 0.2951 1.0000
8.250 1.4098 0.01342 0.00792 -0.1189 0.2831 1.0000
8.500 1.4239 0.01399 0.00842 -0.1168 0.2690 1.0000
8.750 1.4351 0.01469 0.00904 -0.1144 0.2518 1.0000
9.000 1.4427 0.01560 0.00982 -0.1115 0.2301 1.0000
9.250 1.4514 0.01649 0.01061 -0.1089 0.2112 1.0000
9.500 1.4565 0.01760 0.01159 -0.1059 0.1885 1.0000
9.750 1.4656 0.01855 0.01247 -0.1036 0.1751 1.0000
10.000 1.4769 0.01941 0.01330 -0.1016 0.1668 1.0000
10.250 1.4874 0.02034 0.01420 -0.0996 0.1579 1.0000
10.500 1.4989 0.02125 0.01509 -0.0978 0.1510 1.0000
10.750 1.5114 0.02213 0.01596 -0.0962 0.1459 1.0000
11.000 1.5226 0.02312 0.01695 -0.0945 0.1411 1.0000
11.250 1.5363 0.02397 0.01782 -0.0932 0.1374 1.0000
11.500 1.5483 0.02498 0.01883 -0.0917 0.1333 1.0000
11.750 1.5587 0.02612 0.01996 -0.0902 0.1289 1.0000
12.000 1.5711 0.02716 0.02103 -0.0889 0.1261 1.0000
12.250 1.5829 0.02826 0.02215 -0.0877 0.1224 1.0000
12.500 1.5921 0.02960 0.02349 -0.0863 0.1181 1.0000
12.750 1.6013 0.03098 0.02488 -0.0850 0.1138 1.0000
13.000 1.6117 0.03229 0.02622 -0.0839 0.1102 1.0000
13.250 1.6185 0.03394 0.02787 -0.0826 0.1057 1.0000
13.500 1.6269 0.03546 0.02941 -0.0815 0.1020 1.0000
13.750 1.6335 0.03719 0.03115 -0.0803 0.0969 1.0000
14.000 1.6379 0.03913 0.03310 -0.0791 0.0921 1.0000
14.250 1.6414 0.04117 0.03513 -0.0779 0.0859 1.0000
14.500 1.6416 0.04354 0.03750 -0.0766 0.0787 1.0000
14.750 1.6408 0.04607 0.04002 -0.0754 0.0724 1.0000
15.000 1.6394 0.04869 0.04264 -0.0743 0.0668 1.0000
15.250 1.6392 0.05126 0.04523 -0.0733 0.0627 1.0000
15.500 1.6384 0.05393 0.04793 -0.0724 0.0597 1.0000
15.750 1.6398 0.05641 0.05044 -0.0716 0.0574 1.0000
16.000 1.6390 0.05918 0.05326 -0.0709 0.0552 1.0000
16.250 1.6389 0.06194 0.05605 -0.0703 0.0533 1.0000
16.500 1.6406 0.06452 0.05868 -0.0698 0.0519 1.0000
16.750 1.6396 0.06742 0.06163 -0.0693 0.0502 1.0000
17.000 1.6374 0.07053 0.06479 -0.0689 0.0488 1.0000
17.250 1.6385 0.07328 0.06759 -0.0687 0.0477 1.0000
17.500 1.6394 0.07611 0.07048 -0.0685 0.0469 1.0000
17.750 1.6401 0.07895 0.07338 -0.0684 0.0459 1.0000
18.000 1.6395 0.08201 0.07649 -0.0683 0.0450 1.0000
18.250 1.6376 0.08527 0.07980 -0.0684 0.0440 1.0000
18.500 1.6364 0.08847 0.08305 -0.0685 0.0431 1.0000
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