GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 592 AIRFOIL (goe592-il) Reynolds number: 200,000 Max Cl/Cd: 76.16 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe592-il-200000-n5.txt Download as CSV file: xf-goe592-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 592 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.0776 0.10778 0.10344 -0.1287 0.9256 0.0452
-11.750 0.0803 0.10493 0.10058 -0.1303 0.9184 0.0453
-11.500 0.0923 0.10182 0.09744 -0.1324 0.9136 0.0453
-11.250 0.1018 0.09879 0.09438 -0.1342 0.9083 0.0453
-11.000 0.1068 0.09491 0.09049 -0.1347 0.9013 0.0408
-10.750 0.1270 0.09374 0.08930 -0.1354 0.8963 0.0439
-10.500 0.1338 0.09103 0.08658 -0.1364 0.8901 0.0434
-10.250 0.1391 0.08846 0.08399 -0.1372 0.8829 0.0437
-10.000 0.1467 0.08543 0.08092 -0.1388 0.8774 0.0428
-9.750 0.1434 0.08199 0.07747 -0.1397 0.8690 0.0413
-9.500 0.1477 0.07917 0.07462 -0.1407 0.8621 0.0413
-9.250 0.1541 0.07689 0.07232 -0.1413 0.8554 0.0416
-9.000 0.1602 0.07493 0.07036 -0.1415 0.8478 0.0424
-8.750 0.1659 0.07243 0.06781 -0.1425 0.8418 0.0429
-8.500 0.1653 0.06997 0.06537 -0.1426 0.8333 0.0431
-8.250 0.1659 0.06721 0.06258 -0.1433 0.8260 0.0430
-8.000 0.1627 0.06455 0.05992 -0.1435 0.8179 0.0430
-7.750 0.1567 0.06188 0.05723 -0.1435 0.8097 0.0431
-7.500 0.1507 0.05904 0.05437 -0.1444 0.8023 0.0433
-7.250 0.1466 0.05540 0.05071 -0.1467 0.7941 0.0440
-6.750 0.1175 0.03736 0.03210 -0.1585 0.7780 0.0456
-6.500 0.1347 0.03515 0.02971 -0.1591 0.7727 0.0461
-6.250 0.1526 0.03350 0.02792 -0.1591 0.7671 0.0468
-6.000 0.1523 0.02625 0.01986 -0.1594 0.7605 0.0495
-5.750 0.1683 0.02298 0.01595 -0.1590 0.7556 0.0511
-5.500 0.1929 0.02247 0.01534 -0.1586 0.7506 0.0519
-5.250 0.2150 0.02182 0.01458 -0.1578 0.7445 0.0528
-5.000 0.2393 0.02091 0.01341 -0.1574 0.7395 0.0545
-4.750 0.2648 0.01967 0.01175 -0.1572 0.7353 0.0567
-4.500 0.2875 0.01944 0.01153 -0.1563 0.7291 0.0577
-4.250 0.3127 0.01906 0.01106 -0.1558 0.7237 0.0590
-4.000 0.3397 0.01849 0.01028 -0.1557 0.7193 0.0608
-3.750 0.3642 0.01792 0.00948 -0.1550 0.7142 0.0631
-3.500 0.3886 0.01773 0.00932 -0.1544 0.7085 0.0646
-3.250 0.4153 0.01748 0.00898 -0.1541 0.7037 0.0667
-3.000 0.4428 0.01711 0.00842 -0.1539 0.6994 0.0692
-2.750 0.4660 0.01683 0.00810 -0.1530 0.6937 0.0712
-2.500 0.4915 0.01665 0.00792 -0.1526 0.6885 0.0733
-2.250 0.5190 0.01642 0.00759 -0.1524 0.6842 0.0761
-2.000 0.5443 0.01626 0.00731 -0.1518 0.6793 0.0788
-1.750 0.5680 0.01602 0.00713 -0.1511 0.6739 0.0811
-1.500 0.5940 0.01586 0.00694 -0.1507 0.6691 0.0837
-1.250 0.6220 0.01571 0.00669 -0.1506 0.6651 0.0868
-1.000 0.6449 0.01557 0.00656 -0.1496 0.6598 0.0893
-0.750 0.6688 0.01543 0.00646 -0.1489 0.6548 0.0920
-0.500 0.6950 0.01534 0.00634 -0.1485 0.6502 0.0953
-0.250 0.7221 0.01526 0.00620 -0.1483 0.6461 0.0985
0.000 0.7439 0.01519 0.00618 -0.1471 0.6408 0.1013
0.250 0.7679 0.01514 0.00616 -0.1464 0.6358 0.1052
0.500 0.7941 0.01510 0.00608 -0.1460 0.6314 0.1095
0.750 0.8193 0.01508 0.00605 -0.1455 0.6271 0.1139
1.000 0.8410 0.01509 0.00613 -0.1444 0.6219 0.1197
1.250 0.8649 0.01510 0.00615 -0.1436 0.6169 0.1275
1.500 0.8912 0.01509 0.00614 -0.1433 0.6126 0.1397
1.750 0.9138 0.01511 0.00624 -0.1423 0.6078 0.1588
2.000 0.9347 0.01511 0.00638 -0.1411 0.6025 0.1955
2.250 0.9574 0.01500 0.00649 -0.1402 0.5977 0.2788
2.750 1.0295 0.01406 0.00696 -0.1440 0.5879 1.0000
3.000 1.0504 0.01424 0.00709 -0.1427 0.5825 1.0000
3.250 1.0744 0.01440 0.00716 -0.1419 0.5776 1.0000
3.500 1.0957 0.01460 0.00731 -0.1407 0.5727 1.0000
3.750 1.1139 0.01481 0.00752 -0.1389 0.5667 1.0000
4.000 1.1352 0.01500 0.00764 -0.1377 0.5614 1.0000
4.250 1.1569 0.01519 0.00778 -0.1366 0.5564 1.0000
4.500 1.1707 0.01543 0.00804 -0.1340 0.5500 1.0000
4.750 1.1895 0.01564 0.00820 -0.1324 0.5440 1.0000
5.000 1.2081 0.01587 0.00839 -0.1308 0.5381 1.0000
5.250 1.2221 0.01616 0.00870 -0.1283 0.5309 1.0000
5.500 1.2411 0.01639 0.00887 -0.1268 0.5245 1.0000
5.750 1.2561 0.01672 0.00921 -0.1247 0.5179 1.0000
6.000 1.2723 0.01703 0.00952 -0.1228 0.5111 1.0000
6.250 1.2897 0.01733 0.00978 -0.1211 0.5044 1.0000
6.500 1.3021 0.01773 0.01020 -0.1187 0.4959 1.0000
6.750 1.3191 0.01807 0.01048 -0.1170 0.4886 1.0000
7.000 1.3310 0.01855 0.01100 -0.1146 0.4802 1.0000
7.250 1.3468 0.01896 0.01136 -0.1129 0.4728 1.0000
7.500 1.3596 0.01947 0.01190 -0.1108 0.4647 1.0000
7.750 1.3731 0.01997 0.01237 -0.1087 0.4563 1.0000
8.000 1.3852 0.02056 0.01299 -0.1066 0.4476 1.0000
8.250 1.3977 0.02115 0.01354 -0.1046 0.4391 1.0000
8.500 1.4102 0.02178 0.01421 -0.1027 0.4312 1.0000
8.750 1.4221 0.02246 0.01488 -0.1007 0.4229 1.0000
9.000 1.4333 0.02320 0.01564 -0.0987 0.4142 1.0000
9.250 1.4427 0.02402 0.01643 -0.0965 0.4045 1.0000
9.500 1.4525 0.02489 0.01733 -0.0945 0.3949 1.0000
9.750 1.4613 0.02582 0.01824 -0.0925 0.3859 1.0000
10.000 1.4691 0.02685 0.01930 -0.0904 0.3751 1.0000
10.250 1.4763 0.02795 0.02040 -0.0883 0.3648 1.0000
10.500 1.4809 0.02924 0.02164 -0.0860 0.3532 1.0000
10.750 1.4870 0.03052 0.02295 -0.0841 0.3414 1.0000
11.000 1.4926 0.03188 0.02432 -0.0822 0.3309 1.0000
11.500 1.5016 0.03492 0.02736 -0.0785 0.3087 1.0000
11.750 1.5050 0.03661 0.02905 -0.0767 0.2976 1.0000
12.000 1.5065 0.03851 0.03092 -0.0749 0.2863 1.0000
12.250 1.5094 0.04037 0.03280 -0.0733 0.2747 1.0000
12.500 1.5117 0.04234 0.03478 -0.0718 0.2636 1.0000
12.750 1.5119 0.04455 0.03698 -0.0703 0.2527 1.0000
13.000 1.5121 0.04683 0.03926 -0.0689 0.2411 1.0000
13.250 1.5123 0.04919 0.04162 -0.0676 0.2292 1.0000
13.500 1.5105 0.05179 0.04421 -0.0664 0.2170 1.0000
13.750 1.5070 0.05465 0.04705 -0.0652 0.2043 1.0000
14.000 1.5033 0.05760 0.04999 -0.0642 0.1911 1.0000
14.250 1.4985 0.06075 0.05312 -0.0632 0.1766 1.0000
14.500 1.4926 0.06411 0.05645 -0.0624 0.1615 1.0000
14.750 1.4863 0.06761 0.05992 -0.0617 0.1485 1.0000
15.000 1.4794 0.07124 0.06353 -0.0611 0.1374 1.0000
15.250 1.4756 0.07459 0.06689 -0.0607 0.1292 1.0000
15.500 1.4705 0.07815 0.07045 -0.0604 0.1231 1.0000
15.750 1.4692 0.08130 0.07365 -0.0603 0.1182 1.0000
16.000 1.4666 0.08464 0.07702 -0.0602 0.1141 1.0000
16.250 1.4636 0.08808 0.08049 -0.0602 0.1107 1.0000
16.500 1.4650 0.09097 0.08346 -0.0602 0.1078 1.0000
16.750 1.4656 0.09398 0.08654 -0.0603 0.1051 1.0000
17.000 1.4653 0.09712 0.08973 -0.0605 0.1027 1.0000
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