GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 600 AIRFOIL (goe600-il) Reynolds number: 100,000 Max Cl/Cd: 49.42 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe600-il-100000-n5.txt Download as CSV file: xf-goe600-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 600 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7348 0.07340 0.06791 -0.0482 1.0000 0.0279
-12.250 -0.7577 0.06599 0.06031 -0.0538 1.0000 0.0278
-12.000 -0.7791 0.05974 0.05384 -0.0581 1.0000 0.0278
-11.750 -0.7992 0.05465 0.04847 -0.0605 1.0000 0.0279
-11.500 -0.8115 0.05112 0.04478 -0.0608 1.0000 0.0282
-11.250 -0.8152 0.04887 0.04246 -0.0597 1.0000 0.0288
-11.000 -0.8174 0.04688 0.04037 -0.0582 1.0000 0.0294
-10.750 -0.8168 0.04473 0.03805 -0.0568 1.0000 0.0302
-10.500 -0.8148 0.04241 0.03549 -0.0552 1.0000 0.0312
-10.250 -0.8110 0.03999 0.03278 -0.0535 1.0000 0.0322
-10.000 -0.8047 0.03765 0.03012 -0.0516 1.0000 0.0334
-9.750 -0.7964 0.03560 0.02771 -0.0497 1.0000 0.0350
-9.500 -0.7852 0.03425 0.02639 -0.0481 1.0000 0.0366
-9.250 -0.7739 0.03303 0.02508 -0.0462 1.0000 0.0386
-9.000 -0.7626 0.03162 0.02344 -0.0441 1.0000 0.0408
-8.750 -0.7504 0.03030 0.02182 -0.0419 1.0000 0.0431
-8.500 -0.7401 0.02898 0.02056 -0.0398 1.0000 0.0457
-8.250 -0.7284 0.02802 0.01953 -0.0377 1.0000 0.0489
-8.000 -0.7156 0.02702 0.01834 -0.0355 1.0000 0.0525
-7.750 -0.6971 0.02578 0.01707 -0.0347 0.9979 0.0567
-7.500 -0.6649 0.02468 0.01584 -0.0365 0.9923 0.0631
-7.250 -0.6328 0.02364 0.01478 -0.0383 0.9863 0.0700
-7.000 -0.6000 0.02284 0.01392 -0.0399 0.9801 0.0785
-6.750 -0.5653 0.02218 0.01320 -0.0419 0.9745 0.0883
-6.500 -0.5327 0.02154 0.01252 -0.0434 0.9679 0.0997
-6.250 -0.4982 0.02086 0.01179 -0.0453 0.9624 0.1137
-6.000 -0.4663 0.02023 0.01110 -0.0466 0.9557 0.1296
-5.750 -0.4336 0.01964 0.01045 -0.0480 0.9491 0.1474
-5.500 -0.4021 0.01907 0.00983 -0.0492 0.9425 0.1635
-5.250 -0.3720 0.01852 0.00930 -0.0500 0.9350 0.1802
-5.000 -0.3404 0.01794 0.00881 -0.0512 0.9293 0.2015
-4.750 -0.3132 0.01743 0.00843 -0.0515 0.9207 0.2321
-4.500 -0.2823 0.01688 0.00808 -0.0525 0.9150 0.2847
-4.250 -0.2571 0.01647 0.00787 -0.0522 0.9059 0.3419
-4.000 -0.2279 0.01609 0.00767 -0.0526 0.9001 0.4020
-3.750 -0.2021 0.01589 0.00759 -0.0523 0.8917 0.4472
-3.500 -0.1730 0.01572 0.00744 -0.0524 0.8856 0.4820
-3.250 -0.1462 0.01563 0.00734 -0.0521 0.8777 0.5099
-3.000 -0.1177 0.01553 0.00721 -0.0521 0.8713 0.5359
-2.750 -0.0906 0.01547 0.00715 -0.0519 0.8646 0.5606
-2.500 -0.0635 0.01539 0.00708 -0.0516 0.8579 0.5879
-2.250 -0.0359 0.01531 0.00701 -0.0514 0.8521 0.6142
-2.000 -0.0099 0.01526 0.00700 -0.0509 0.8448 0.6381
-1.750 0.0182 0.01518 0.00692 -0.0507 0.8399 0.6620
-1.500 0.0439 0.01516 0.00696 -0.0502 0.8328 0.6859
-1.250 0.0707 0.01510 0.00695 -0.0496 0.8270 0.7129
-1.000 0.0970 0.01506 0.00698 -0.0490 0.8215 0.7421
-0.750 0.1223 0.01505 0.00704 -0.0481 0.8144 0.7718
-0.500 0.1494 0.01495 0.00698 -0.0473 0.8079 0.7998
-0.250 0.1755 0.01490 0.00697 -0.0465 0.7979 0.8261
0.000 0.2037 0.01483 0.00690 -0.0460 0.7889 0.8529
0.250 0.2346 0.01479 0.00686 -0.0461 0.7809 0.8805
0.500 0.2690 0.01481 0.00689 -0.0471 0.7737 0.9071
0.750 0.3060 0.01481 0.00688 -0.0487 0.7664 0.9326
1.000 0.3456 0.01483 0.00688 -0.0510 0.7592 0.9557
1.250 0.3867 0.01484 0.00688 -0.0538 0.7512 0.9762
1.500 0.4299 0.01484 0.00686 -0.0571 0.7431 0.9935
1.750 0.4620 0.01484 0.00683 -0.0581 0.7344 1.0000
2.000 0.4842 0.01491 0.00686 -0.0572 0.7251 1.0000
2.250 0.5082 0.01492 0.00682 -0.0564 0.7166 1.0000
2.500 0.5306 0.01503 0.00694 -0.0555 0.7056 1.0000
2.750 0.5543 0.01510 0.00699 -0.0546 0.6951 1.0000
3.000 0.5790 0.01514 0.00699 -0.0538 0.6846 1.0000
3.250 0.6024 0.01524 0.00711 -0.0529 0.6712 1.0000
3.500 0.6261 0.01532 0.00721 -0.0521 0.6571 1.0000
3.750 0.6502 0.01541 0.00730 -0.0512 0.6420 1.0000
4.000 0.6743 0.01549 0.00742 -0.0504 0.6260 1.0000
4.250 0.6986 0.01559 0.00752 -0.0496 0.6088 1.0000
4.500 0.7223 0.01570 0.00765 -0.0487 0.5885 1.0000
4.750 0.7458 0.01583 0.00780 -0.0477 0.5650 1.0000
5.000 0.7689 0.01598 0.00793 -0.0467 0.5375 1.0000
5.250 0.7917 0.01618 0.00805 -0.0456 0.5057 1.0000
5.500 0.8136 0.01648 0.00820 -0.0444 0.4718 1.0000
5.750 0.8347 0.01689 0.00845 -0.0432 0.4405 1.0000
6.000 0.8556 0.01739 0.00881 -0.0420 0.4121 1.0000
6.250 0.8765 0.01791 0.00926 -0.0409 0.3873 1.0000
6.500 0.8973 0.01845 0.00976 -0.0398 0.3644 1.0000
6.750 0.9181 0.01899 0.01028 -0.0388 0.3420 1.0000
7.000 0.9383 0.01955 0.01083 -0.0377 0.3200 1.0000
7.250 0.9580 0.02014 0.01140 -0.0365 0.2985 1.0000
7.500 0.9768 0.02077 0.01202 -0.0352 0.2751 1.0000
7.750 0.9944 0.02146 0.01267 -0.0339 0.2505 1.0000
8.000 1.0104 0.02224 0.01336 -0.0323 0.2253 1.0000
8.250 1.0260 0.02306 0.01410 -0.0308 0.2004 1.0000
8.500 1.0410 0.02393 0.01491 -0.0292 0.1786 1.0000
8.750 1.0558 0.02480 0.01579 -0.0276 0.1600 1.0000
9.000 1.0694 0.02573 0.01670 -0.0259 0.1429 1.0000
9.250 1.0814 0.02672 0.01767 -0.0240 0.1268 1.0000
9.500 1.0908 0.02777 0.01870 -0.0217 0.1122 1.0000
9.750 1.0996 0.02895 0.01985 -0.0196 0.0988 1.0000
10.000 1.1066 0.03032 0.02120 -0.0175 0.0868 1.0000
10.250 1.1138 0.03176 0.02268 -0.0155 0.0762 1.0000
10.500 1.1203 0.03330 0.02432 -0.0136 0.0672 1.0000
10.750 1.1253 0.03500 0.02603 -0.0119 0.0602 1.0000
11.000 1.1325 0.03660 0.02776 -0.0103 0.0541 1.0000
11.250 1.1366 0.03847 0.02965 -0.0089 0.0500 1.0000
11.500 1.1421 0.04031 0.03161 -0.0076 0.0461 1.0000
11.750 1.1450 0.04241 0.03376 -0.0065 0.0433 1.0000
12.000 1.1461 0.04476 0.03618 -0.0054 0.0412 1.0000
12.250 1.1490 0.04704 0.03862 -0.0044 0.0390 1.0000
12.500 1.1508 0.04948 0.04117 -0.0036 0.0370 1.0000
12.750 1.1506 0.05216 0.04395 -0.0031 0.0354 1.0000
13.000 1.1481 0.05514 0.04696 -0.0025 0.0340 1.0000
13.250 1.1500 0.05784 0.04985 -0.0020 0.0329 1.0000
13.500 1.1507 0.06072 0.05292 -0.0016 0.0317 1.0000
13.750 1.1502 0.06379 0.05615 -0.0014 0.0306 1.0000
14.000 1.1485 0.06704 0.05954 -0.0015 0.0296 1.0000
14.250 1.1457 0.07046 0.06308 -0.0018 0.0287 1.0000
14.500 1.1426 0.07397 0.06667 -0.0022 0.0279 1.0000
14.750 1.1401 0.07752 0.07026 -0.0025 0.0271 1.0000
15.000 1.1336 0.08192 0.07488 -0.0036 0.0265 1.0000
15.250 1.1256 0.08672 0.07994 -0.0051 0.0261 1.0000
15.500 1.1161 0.09197 0.08542 -0.0070 0.0257 1.0000
15.750 1.1048 0.09773 0.09141 -0.0094 0.0254 1.0000
16.000 1.0914 0.10412 0.09803 -0.0124 0.0252 1.0000
16.250 1.0758 0.11129 0.10542 -0.0162 0.0251 1.0000
16.500 1.0574 0.11942 0.11377 -0.0208 0.0250 1.0000
16.750 1.0353 0.12888 0.12345 -0.0265 0.0251 1.0000
17.000 1.0078 0.14037 0.13515 -0.0337 0.0254 1.0000
17.250 0.9694 0.15611 0.15106 -0.0434 0.0259 1.0000
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