GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 100,000 Max Cl/Cd: 62.07 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe371-il-100000-n5.txt Download as CSV file: xf-goe371-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3143 0.09631 0.09162 -0.0296 1.0000 0.0375
-7.500 -0.3227 0.09505 0.09048 -0.0288 1.0000 0.0378
-7.250 -0.3300 0.09366 0.08920 -0.0292 1.0000 0.0382
-7.000 -0.3341 0.09194 0.08757 -0.0299 1.0000 0.0384
-6.750 -0.3371 0.09002 0.08572 -0.0305 1.0000 0.0385
-6.500 -0.3299 0.08720 0.08291 -0.0338 0.9982 0.0387
-6.250 -0.2985 0.08212 0.07775 -0.0431 0.9911 0.0388
-6.000 -0.2919 0.07665 0.07237 -0.0402 0.9875 0.0401
-5.750 -0.2719 0.07285 0.06855 -0.0423 0.9817 0.0418
-5.500 -0.2435 0.06898 0.06462 -0.0481 0.9758 0.0466
-5.250 -0.1979 0.06315 0.05859 -0.0627 0.9670 0.0522
-5.000 -0.1822 0.06001 0.05546 -0.0622 0.9615 0.0548
-4.750 -0.1258 0.05592 0.05088 -0.0755 0.9541 0.0643
-4.500 -0.1034 0.05074 0.04572 -0.0779 0.9472 0.0659
-4.250 -0.0779 0.04795 0.04295 -0.0792 0.9408 0.0730
-4.000 -0.0294 0.04061 0.03506 -0.0868 0.9345 0.0476
-3.750 0.0072 0.03618 0.03025 -0.0905 0.9270 0.0449
-3.500 0.0443 0.03269 0.02629 -0.0935 0.9204 0.0477
-3.250 0.0777 0.02943 0.02256 -0.0952 0.9128 0.0471
-3.000 0.1122 0.02673 0.01934 -0.0967 0.9061 0.0479
-2.750 0.1449 0.02482 0.01687 -0.0974 0.8981 0.0503
-2.500 0.1772 0.02301 0.01462 -0.0982 0.8917 0.0503
-2.250 0.2072 0.02162 0.01287 -0.0984 0.8844 0.0506
-2.000 0.2394 0.02036 0.01130 -0.0990 0.8785 0.0516
-1.750 0.2674 0.01935 0.01023 -0.0991 0.8704 0.0549
-1.500 0.2983 0.01849 0.00920 -0.0994 0.8637 0.0560
-1.250 0.3271 0.01774 0.00834 -0.0992 0.8556 0.0564
-1.000 0.3560 0.01710 0.00763 -0.0991 0.8476 0.0570
-0.750 0.3853 0.01654 0.00700 -0.0991 0.8397 0.0581
-0.500 0.4124 0.01614 0.00655 -0.0987 0.8304 0.0595
-0.250 0.4423 0.01576 0.00608 -0.0987 0.8221 0.0617
0.000 0.4699 0.01551 0.00573 -0.0983 0.8120 0.0644
0.250 0.4975 0.01527 0.00548 -0.0980 0.8018 0.0705
0.500 0.5271 0.01503 0.00526 -0.0980 0.7922 0.0905
1.000 0.5941 0.01287 0.00504 -0.1000 0.7700 1.0000
1.250 0.6210 0.01296 0.00497 -0.0995 0.7578 1.0000
1.500 0.6477 0.01305 0.00495 -0.0989 0.7451 1.0000
1.750 0.6741 0.01316 0.00494 -0.0984 0.7316 1.0000
2.000 0.7002 0.01328 0.00496 -0.0977 0.7172 1.0000
2.250 0.7260 0.01341 0.00503 -0.0970 0.7018 1.0000
2.500 0.7511 0.01354 0.00510 -0.0962 0.6835 1.0000
2.750 0.7761 0.01366 0.00512 -0.0953 0.6626 1.0000
3.000 0.7999 0.01379 0.00518 -0.0942 0.6372 1.0000
3.250 0.8238 0.01394 0.00523 -0.0932 0.6096 1.0000
3.500 0.8480 0.01412 0.00529 -0.0921 0.5839 1.0000
3.750 0.8725 0.01436 0.00540 -0.0913 0.5629 1.0000
4.000 0.8970 0.01464 0.00562 -0.0905 0.5455 1.0000
4.250 0.9215 0.01496 0.00587 -0.0897 0.5292 1.0000
4.500 0.9458 0.01529 0.00618 -0.0890 0.5137 1.0000
4.750 0.9701 0.01565 0.00654 -0.0882 0.4986 1.0000
5.000 0.9942 0.01602 0.00692 -0.0875 0.4843 1.0000
5.250 1.0180 0.01640 0.00732 -0.0867 0.4693 1.0000
5.500 1.0414 0.01678 0.00775 -0.0858 0.4534 1.0000
5.750 1.0645 0.01718 0.00823 -0.0849 0.4368 1.0000
6.000 1.0872 0.01758 0.00871 -0.0840 0.4193 1.0000
6.250 1.1088 0.01801 0.00917 -0.0828 0.3984 1.0000
6.500 1.1290 0.01844 0.00965 -0.0815 0.3697 1.0000
6.750 1.1483 0.01893 0.01017 -0.0801 0.3334 1.0000
7.000 1.1663 0.01955 0.01070 -0.0785 0.2958 1.0000
7.250 1.1841 0.02028 0.01135 -0.0769 0.2665 1.0000
7.500 1.2005 0.02116 0.01211 -0.0753 0.2394 1.0000
7.750 1.2153 0.02218 0.01299 -0.0735 0.2084 1.0000
8.000 1.2300 0.02319 0.01390 -0.0718 0.1797 1.0000
8.250 1.2460 0.02410 0.01486 -0.0703 0.1565 1.0000
8.500 1.2621 0.02498 0.01580 -0.0687 0.1315 1.0000
8.750 1.2722 0.02636 0.01689 -0.0666 0.0852 1.0000
9.000 1.2788 0.02808 0.01838 -0.0640 0.0543 1.0000
9.250 1.2846 0.02981 0.02006 -0.0611 0.0371 1.0000
9.500 1.2897 0.03142 0.02166 -0.0582 0.0298 1.0000
9.750 1.2954 0.03293 0.02330 -0.0555 0.0259 1.0000
10.000 1.2975 0.03476 0.02520 -0.0527 0.0233 1.0000
10.250 1.2989 0.03664 0.02729 -0.0500 0.0222 1.0000
10.500 1.2999 0.03862 0.02949 -0.0475 0.0214 1.0000
10.750 1.2998 0.04078 0.03186 -0.0453 0.0207 1.0000
11.000 1.2993 0.04310 0.03438 -0.0434 0.0198 1.0000
11.250 1.2981 0.04562 0.03708 -0.0418 0.0189 1.0000
11.500 1.2966 0.04830 0.03994 -0.0404 0.0181 1.0000
11.750 1.2941 0.05121 0.04301 -0.0394 0.0172 1.0000
12.000 1.2913 0.05431 0.04627 -0.0386 0.0166 1.0000
12.250 1.2882 0.05762 0.04974 -0.0379 0.0162 1.0000
12.500 1.2854 0.06109 0.05338 -0.0374 0.0158 1.0000
12.750 1.2821 0.06480 0.05727 -0.0370 0.0155 1.0000
13.000 1.2793 0.06862 0.06128 -0.0368 0.0153 1.0000
13.250 1.2744 0.07291 0.06580 -0.0369 0.0150 1.0000
13.500 1.2679 0.07753 0.07065 -0.0374 0.0149 1.0000
13.750 1.2586 0.08270 0.07608 -0.0385 0.0147 1.0000
14.000 1.2483 0.08808 0.08169 -0.0402 0.0147 1.0000
14.250 1.2363 0.09399 0.08780 -0.0425 0.0147 1.0000
14.500 1.2234 0.10026 0.09429 -0.0454 0.0147 1.0000
14.750 1.2098 0.10700 0.10125 -0.0489 0.0147 1.0000
15.250 1.1821 0.12161 0.11629 -0.0574 0.0147 1.0000
15.500 1.1681 0.12959 0.12444 -0.0624 0.0148 1.0000
15.750 1.1549 0.13789 0.13290 -0.0677 0.0149 1.0000
16.000 1.1408 0.14710 0.14226 -0.0737 0.0151 1.0000
16.250 1.1247 0.15785 0.15315 -0.0807 0.0154 1.0000
16.500 1.0983 0.17391 0.16934 -0.0903 0.0161 1.0000
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Polar data table (+)
Polar graphs
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