GOE 567 AIRFOIL (goe567-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 567 AIRFOIL (goe567-il) Reynolds number: 200,000 Max Cl/Cd: 80.99 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe567-il-200000.txt Download as CSV file: xf-goe567-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 567 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2784 0.11013 0.10668 -0.0500 0.9953 0.0895
-10.250 -0.3002 0.10158 0.09815 -0.0677 0.9862 0.0970
-10.000 -0.4665 0.04672 0.04259 -0.1211 0.9562 0.0738
-9.500 -0.3288 0.06321 0.05965 -0.0992 0.9619 0.0839
-9.250 -0.3770 0.03909 0.03456 -0.1343 0.9394 0.0823
-9.000 -0.3626 0.03541 0.03019 -0.1384 0.9271 0.0844
-8.750 -0.3336 0.03140 0.02599 -0.1424 0.9231 0.0870
-8.500 -0.3093 0.03047 0.02507 -0.1424 0.9129 0.0893
-8.250 -0.2767 0.02858 0.02292 -0.1449 0.9078 0.0918
-8.000 -0.2544 0.02700 0.02102 -0.1452 0.8977 0.0940
-7.750 -0.2235 0.02560 0.01921 -0.1468 0.8917 0.0964
-7.500 -0.2010 0.02384 0.01716 -0.1469 0.8822 0.0981
-7.250 -0.1717 0.02239 0.01565 -0.1478 0.8758 0.1005
-7.000 -0.1460 0.02165 0.01482 -0.1477 0.8673 0.1030
-6.750 -0.1174 0.02083 0.01383 -0.1480 0.8601 0.1056
-6.500 -0.0905 0.02009 0.01289 -0.1480 0.8526 0.1079
-6.250 -0.0630 0.01953 0.01212 -0.1479 0.8449 0.1102
-6.000 -0.0356 0.01846 0.01094 -0.1481 0.8384 0.1131
-5.750 -0.0101 0.01790 0.01038 -0.1478 0.8302 0.1159
-5.500 0.0191 0.01738 0.00976 -0.1480 0.8242 0.1190
-5.250 0.0445 0.01702 0.00931 -0.1475 0.8162 0.1223
-5.000 0.0727 0.01662 0.00877 -0.1475 0.8095 0.1256
-4.750 0.0989 0.01604 0.00824 -0.1472 0.8027 0.1297
-4.500 0.1255 0.01572 0.00789 -0.1470 0.7954 0.1339
-4.250 0.1549 0.01545 0.00750 -0.1471 0.7897 0.1391
-4.000 0.1794 0.01507 0.00720 -0.1466 0.7818 0.1454
-3.750 0.2076 0.01481 0.00690 -0.1465 0.7754 0.1533
-3.500 0.2345 0.01451 0.00664 -0.1464 0.7690 0.1640
-3.250 0.2610 0.01421 0.00641 -0.1462 0.7617 0.1840
-3.000 0.2897 0.01378 0.00616 -0.1465 0.7560 0.2351
-2.750 0.3151 0.01362 0.00622 -0.1461 0.7486 0.2925
-2.500 0.3430 0.01361 0.00623 -0.1460 0.7421 0.3296
-2.250 0.3715 0.01369 0.00627 -0.1459 0.7362 0.3578
-2.000 0.3974 0.01376 0.00638 -0.1454 0.7286 0.3794
-1.750 0.4263 0.01383 0.00639 -0.1454 0.7228 0.3992
-1.500 0.4528 0.01393 0.00650 -0.1450 0.7162 0.4161
-1.250 0.4800 0.01400 0.00655 -0.1447 0.7093 0.4320
-1.000 0.5094 0.01409 0.00657 -0.1448 0.7040 0.4490
-0.750 0.5343 0.01421 0.00675 -0.1441 0.6966 0.4654
-0.500 0.5621 0.01430 0.00681 -0.1439 0.6905 0.4818
-0.250 0.5906 0.01441 0.00686 -0.1438 0.6851 0.4970
0.000 0.6156 0.01448 0.00701 -0.1431 0.6778 0.5106
0.250 0.6437 0.01453 0.00705 -0.1430 0.6721 0.5255
0.500 0.6706 0.01463 0.00716 -0.1427 0.6664 0.5397
0.750 0.6966 0.01469 0.00725 -0.1422 0.6596 0.5527
1.000 0.7255 0.01471 0.00720 -0.1422 0.6542 0.5661
1.250 0.7507 0.01474 0.00731 -0.1416 0.6471 0.5777
1.500 0.7776 0.01472 0.00730 -0.1413 0.6404 0.5902
1.750 0.8057 0.01472 0.00725 -0.1412 0.6344 0.6039
2.000 0.8303 0.01472 0.00732 -0.1405 0.6264 0.6178
2.250 0.8587 0.01468 0.00725 -0.1404 0.6204 0.6328
2.500 0.8834 0.01472 0.00739 -0.1397 0.6138 0.6477
2.750 0.9097 0.01472 0.00746 -0.1393 0.6077 0.6645
3.000 0.9384 0.01471 0.00745 -0.1394 0.6029 0.6842
3.250 0.9613 0.01473 0.00765 -0.1384 0.5962 0.7060
3.500 0.9864 0.01466 0.00772 -0.1378 0.5905 0.7381
3.750 1.0102 0.01438 0.00771 -0.1365 0.5859 0.8316
4.000 1.0400 0.01444 0.00790 -0.1370 0.5787 1.0000
4.250 1.0685 0.01457 0.00794 -0.1371 0.5724 1.0000
4.500 1.0938 0.01472 0.00806 -0.1366 0.5647 1.0000
4.750 1.1197 0.01481 0.00808 -0.1362 0.5564 1.0000
5.000 1.1444 0.01497 0.00822 -0.1356 0.5483 1.0000
5.250 1.1696 0.01512 0.00834 -0.1350 0.5407 1.0000
5.500 1.1951 0.01531 0.00851 -0.1345 0.5337 1.0000
5.750 1.2187 0.01551 0.00875 -0.1338 0.5263 1.0000
6.250 1.2673 0.01595 0.00920 -0.1324 0.5125 1.0000
6.500 1.2925 0.01614 0.00935 -0.1319 0.5054 1.0000
6.750 1.3139 0.01638 0.00966 -0.1308 0.4973 1.0000
7.000 1.3373 0.01657 0.00982 -0.1299 0.4892 1.0000
7.250 1.3577 0.01681 0.01015 -0.1286 0.4807 1.0000
7.500 1.3801 0.01704 0.01037 -0.1276 0.4730 1.0000
7.750 1.3997 0.01731 0.01071 -0.1261 0.4646 1.0000
8.000 1.4205 0.01755 0.01096 -0.1249 0.4563 1.0000
8.250 1.4382 0.01784 0.01134 -0.1231 0.4473 1.0000
8.750 1.4719 0.01843 0.01202 -0.1193 0.4280 1.0000
9.000 1.4866 0.01876 0.01238 -0.1171 0.4183 1.0000
9.250 1.4977 0.01911 0.01276 -0.1142 0.4074 1.0000
9.500 1.5063 0.01955 0.01326 -0.1109 0.3949 1.0000
9.750 1.5155 0.02005 0.01381 -0.1080 0.3829 1.0000
10.000 1.5233 0.02065 0.01443 -0.1049 0.3699 1.0000
10.250 1.5286 0.02138 0.01518 -0.1017 0.3545 1.0000
10.500 1.5315 0.02229 0.01609 -0.0983 0.3361 1.0000
10.750 1.5304 0.02349 0.01723 -0.0947 0.3146 1.0000
11.000 1.5258 0.02504 0.01870 -0.0911 0.2899 1.0000
11.250 1.5166 0.02707 0.02060 -0.0874 0.2636 1.0000
11.500 1.5059 0.02948 0.02288 -0.0841 0.2366 1.0000
11.750 1.4948 0.03217 0.02545 -0.0813 0.2114 1.0000
12.000 1.4826 0.03520 0.02836 -0.0788 0.1882 1.0000
12.250 1.4735 0.03818 0.03126 -0.0768 0.1682 1.0000
12.500 1.4643 0.04134 0.03435 -0.0751 0.1530 1.0000
12.750 1.4564 0.04452 0.03749 -0.0737 0.1422 1.0000
13.000 1.4478 0.04794 0.04086 -0.0726 0.1336 1.0000
13.250 1.4440 0.05098 0.04393 -0.0717 0.1255 1.0000
13.500 1.4355 0.05460 0.04751 -0.0708 0.1192 1.0000
13.750 1.4365 0.05734 0.05034 -0.0703 0.1126 1.0000
14.000 1.4327 0.06064 0.05363 -0.0698 0.1070 1.0000
14.250 1.4338 0.06349 0.05654 -0.0694 0.1017 1.0000
14.500 1.4365 0.06624 0.05937 -0.0692 0.0965 1.0000
14.750 1.4357 0.06938 0.06250 -0.0691 0.0925 1.0000
15.000 1.4415 0.07188 0.06514 -0.0691 0.0881 1.0000
15.250 1.4455 0.07462 0.06797 -0.0692 0.0841 1.0000
15.500 1.4458 0.07786 0.07120 -0.0694 0.0808 1.0000
15.750 1.4510 0.08053 0.07399 -0.0696 0.0771 1.0000
16.000 1.4530 0.08369 0.07722 -0.0701 0.0734 1.0000
16.250 1.4518 0.08728 0.08080 -0.0706 0.0702 1.0000
16.500 1.4534 0.09050 0.08413 -0.0711 0.0666 1.0000
16.750 1.4511 0.09432 0.08795 -0.0718 0.0632 1.0000
17.000 1.4496 0.09791 0.09156 -0.0724 0.0597 1.0000
17.250 1.4474 0.10172 0.09544 -0.0731 0.0558 1.0000
17.500 1.4455 0.10517 0.09884 -0.0734 0.0516 1.0000
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