GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 298 AIRFOIL (goe298-il) Reynolds number: 500,000 Max Cl/Cd: 91.71 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe298-il-500000.txt Download as CSV file: xf-goe298-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 298 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3853 0.13653 0.13397 -0.0075 1.0000 0.0483
-11.750 -0.3759 0.13388 0.13133 -0.0085 1.0000 0.0489
-11.500 -0.8012 0.03690 0.03367 -0.0835 1.0000 0.0502
-11.250 -0.7681 0.03988 0.03683 -0.0804 1.0000 0.0505
-11.000 -0.7392 0.04189 0.03894 -0.0783 1.0000 0.0509
-10.750 -0.7092 0.04400 0.04112 -0.0761 1.0000 0.0513
-10.500 -0.6772 0.04629 0.04349 -0.0738 0.9986 0.0516
-10.250 -0.6355 0.04909 0.04636 -0.0720 0.9870 0.0520
-10.000 -0.5939 0.05201 0.04932 -0.0698 0.9732 0.0522
-9.750 -0.6407 0.02122 0.01639 -0.0954 0.9371 0.0566
-9.500 -0.6170 0.02024 0.01512 -0.0950 0.9238 0.0576
-9.250 -0.5932 0.01938 0.01419 -0.0945 0.9120 0.0585
-9.000 -0.5675 0.01918 0.01397 -0.0939 0.9012 0.0593
-8.750 -0.5407 0.01896 0.01372 -0.0935 0.8905 0.0603
-8.500 -0.5145 0.01859 0.01322 -0.0931 0.8810 0.0615
-8.250 -0.4878 0.01796 0.01241 -0.0929 0.8708 0.0629
-8.000 -0.4616 0.01725 0.01156 -0.0927 0.8617 0.0641
-7.750 -0.4337 0.01708 0.01141 -0.0925 0.8515 0.0651
-7.500 -0.4058 0.01696 0.01126 -0.0922 0.8425 0.0661
-7.250 -0.3777 0.01667 0.01090 -0.0920 0.8323 0.0674
-7.000 -0.3499 0.01622 0.01027 -0.0919 0.8233 0.0690
-6.750 -0.3219 0.01571 0.00965 -0.0918 0.8132 0.0704
-6.500 -0.2934 0.01569 0.00964 -0.0916 0.8042 0.0715
-6.250 -0.2646 0.01566 0.00961 -0.0915 0.7941 0.0727
-6.000 -0.2361 0.01546 0.00929 -0.0913 0.7842 0.0742
-5.750 -0.2075 0.01512 0.00878 -0.0912 0.7734 0.0759
-5.500 -0.1792 0.01475 0.00833 -0.0911 0.7637 0.0774
-5.250 -0.1503 0.01477 0.00836 -0.0910 0.7537 0.0786
-5.000 -0.1214 0.01477 0.00830 -0.0909 0.7443 0.0800
-4.750 -0.0924 0.01459 0.00804 -0.0908 0.7342 0.0817
-4.500 -0.0634 0.01444 0.00771 -0.0907 0.7251 0.0836
-4.250 -0.0345 0.01404 0.00730 -0.0908 0.7158 0.0852
-4.000 -0.0057 0.01404 0.00727 -0.0906 0.7073 0.0866
-3.750 0.0238 0.01391 0.00713 -0.0907 0.6985 0.0882
-3.500 0.0529 0.01381 0.00693 -0.0906 0.6894 0.0902
-3.250 0.0825 0.01375 0.00677 -0.0906 0.6798 0.0920
-3.000 0.1112 0.01324 0.00623 -0.0906 0.6697 0.0940
-2.750 0.1405 0.01311 0.00611 -0.0906 0.6602 0.0955
-2.500 0.1697 0.01302 0.00597 -0.0906 0.6508 0.0975
-2.250 0.1992 0.01291 0.00581 -0.0906 0.6420 0.0997
-2.000 0.2286 0.01286 0.00567 -0.0906 0.6326 0.1013
-1.750 0.2577 0.01236 0.00514 -0.0907 0.6242 0.1035
-1.500 0.2869 0.01221 0.00501 -0.0907 0.6151 0.1055
-1.250 0.3161 0.01212 0.00488 -0.0907 0.6071 0.1076
-1.000 0.3455 0.01199 0.00473 -0.0907 0.5988 0.1096
-0.750 0.3747 0.01196 0.00462 -0.0907 0.5913 0.1115
-0.500 0.4041 0.01167 0.00431 -0.0908 0.5845 0.1136
-0.250 0.4332 0.01145 0.00411 -0.0908 0.5777 0.1157
0.000 0.4622 0.01139 0.00402 -0.0908 0.5711 0.1178
0.250 0.4916 0.01130 0.00396 -0.0908 0.5641 0.1202
0.500 0.5207 0.01126 0.00387 -0.0908 0.5569 0.1222
0.750 0.5498 0.01125 0.00383 -0.0908 0.5509 0.1237
1.000 0.5791 0.01105 0.00366 -0.0908 0.5442 0.1262
1.250 0.6079 0.01097 0.00357 -0.0908 0.5355 0.1287
1.500 0.6371 0.01091 0.00354 -0.0908 0.5267 0.1310
1.750 0.6659 0.01093 0.00352 -0.0908 0.5167 0.1336
2.000 0.6949 0.01091 0.00351 -0.0908 0.5070 0.1362
2.250 0.7234 0.01097 0.00351 -0.0907 0.4950 0.1380
2.500 0.7526 0.01087 0.00345 -0.0907 0.4803 0.1419
2.750 0.7812 0.01088 0.00346 -0.0907 0.4615 0.1461
3.000 0.8092 0.01099 0.00347 -0.0906 0.4263 0.1507
3.250 0.8345 0.01143 0.00359 -0.0902 0.3643 0.1563
3.500 0.8609 0.01176 0.00382 -0.0899 0.3410 0.1661
3.750 0.8881 0.01195 0.00404 -0.0898 0.3281 0.1943
4.000 0.9130 0.01085 0.00447 -0.0899 0.3189 0.8039
4.250 0.9328 0.01072 0.00457 -0.0876 0.3122 1.0000
4.500 0.9605 0.01095 0.00475 -0.0874 0.3058 1.0000
4.750 0.9875 0.01126 0.00498 -0.0872 0.2994 1.0000
5.000 1.0150 0.01151 0.00520 -0.0870 0.2940 1.0000
5.250 1.0427 0.01170 0.00539 -0.0869 0.2887 1.0000
5.500 1.0697 0.01197 0.00561 -0.0866 0.2828 1.0000
5.750 1.0962 0.01229 0.00587 -0.0863 0.2768 1.0000
6.000 1.1240 0.01244 0.00604 -0.0862 0.2715 1.0000
6.250 1.1508 0.01269 0.00626 -0.0859 0.2653 1.0000
6.500 1.1767 0.01301 0.00653 -0.0856 0.2591 1.0000
6.750 1.2041 0.01317 0.00672 -0.0854 0.2532 1.0000
7.000 1.2302 0.01345 0.00696 -0.0851 0.2459 1.0000
7.250 1.2564 0.01370 0.00720 -0.0848 0.2384 1.0000
7.500 1.2820 0.01400 0.00745 -0.0844 0.2284 1.0000
7.750 1.3075 0.01429 0.00771 -0.0840 0.2172 1.0000
8.000 1.3317 0.01467 0.00802 -0.0834 0.2038 1.0000
8.250 1.3546 0.01515 0.00840 -0.0827 0.1884 1.0000
8.500 1.3764 0.01569 0.00884 -0.0819 0.1743 1.0000
8.750 1.3974 0.01627 0.00934 -0.0809 0.1633 1.0000
9.000 1.4178 0.01685 0.00987 -0.0798 0.1550 1.0000
9.250 1.4383 0.01740 0.01039 -0.0788 0.1491 1.0000
9.500 1.4580 0.01796 0.01094 -0.0776 0.1442 1.0000
9.750 1.4747 0.01867 0.01161 -0.0761 0.1396 1.0000
10.000 1.4944 0.01914 0.01212 -0.0749 0.1369 1.0000
10.250 1.5110 0.01970 0.01271 -0.0732 0.1341 1.0000
10.500 1.5244 0.02038 0.01339 -0.0712 0.1317 1.0000
10.750 1.5362 0.02122 0.01424 -0.0691 0.1292 1.0000
11.000 1.5484 0.02211 0.01515 -0.0673 0.1270 1.0000
11.250 1.5645 0.02280 0.01591 -0.0660 0.1253 1.0000
11.500 1.5796 0.02360 0.01677 -0.0647 0.1235 1.0000
11.750 1.5932 0.02453 0.01773 -0.0635 0.1213 1.0000
12.000 1.6051 0.02562 0.01884 -0.0621 0.1193 1.0000
12.250 1.6147 0.02693 0.02016 -0.0607 0.1174 1.0000
12.500 1.6241 0.02828 0.02155 -0.0594 0.1157 1.0000
12.750 1.6386 0.02928 0.02264 -0.0585 0.1146 1.0000
13.000 1.6518 0.03039 0.02382 -0.0576 0.1131 1.0000
13.250 1.6641 0.03161 0.02510 -0.0567 0.1115 1.0000
13.500 1.6748 0.03298 0.02653 -0.0558 0.1097 1.0000
13.750 1.6830 0.03461 0.02818 -0.0549 0.1078 1.0000
14.000 1.6881 0.03655 0.03014 -0.0540 0.1059 1.0000
14.250 1.6976 0.03811 0.03179 -0.0532 0.1046 1.0000
14.500 1.7091 0.03952 0.03329 -0.0527 0.1031 1.0000
14.750 1.7191 0.04107 0.03493 -0.0521 0.1013 1.0000
15.000 1.7270 0.04287 0.03678 -0.0516 0.0992 1.0000
15.250 1.7309 0.04505 0.03899 -0.0510 0.0971 1.0000
15.500 1.7341 0.04734 0.04133 -0.0505 0.0950 1.0000
15.750 1.7449 0.04892 0.04302 -0.0502 0.0925 1.0000
16.000 1.7515 0.05098 0.04515 -0.0499 0.0895 1.0000
16.250 1.7515 0.05382 0.04801 -0.0497 0.0867 1.0000
16.500 1.7602 0.05573 0.05002 -0.0496 0.0829 1.0000
16.750 1.7607 0.05866 0.05297 -0.0496 0.0785 1.0000
17.000 1.7628 0.06143 0.05579 -0.0497 0.0722 1.0000
17.250 1.7575 0.06515 0.05952 -0.0500 0.0644 1.0000
17.500 1.7454 0.06981 0.06419 -0.0505 0.0559 1.0000
17.750 1.7292 0.07512 0.06951 -0.0513 0.0499 1.0000
18.250 1.6964 0.08612 0.08065 -0.0535 0.0445 1.0000
18.500 1.6791 0.09197 0.08660 -0.0549 0.0431 1.0000
18.750 1.6601 0.09820 0.09294 -0.0567 0.0420 1.0000
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