GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 601 AIRFOIL (goe601-il) Reynolds number: 200,000 Max Cl/Cd: 57.44 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe601-il-200000-n5.txt Download as CSV file: xf-goe601-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 601 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7216 0.10208 0.09731 -0.0686 1.0000 0.0314
-17.000 -0.7645 0.09072 0.08568 -0.0753 1.0000 0.0314
-16.750 -0.7921 0.08280 0.07755 -0.0799 1.0000 0.0315
-16.500 -0.8163 0.07599 0.07052 -0.0837 1.0000 0.0317
-16.250 -0.8341 0.07061 0.06496 -0.0863 1.0000 0.0318
-16.000 -0.8377 0.06751 0.06184 -0.0871 1.0000 0.0322
-15.750 -0.8428 0.06434 0.05862 -0.0879 1.0000 0.0325
-15.500 -0.8482 0.06122 0.05544 -0.0887 1.0000 0.0328
-15.250 -0.8542 0.05814 0.05226 -0.0893 1.0000 0.0331
-15.000 -0.8598 0.05526 0.04931 -0.0897 1.0000 0.0335
-14.750 -0.8654 0.05248 0.04644 -0.0899 1.0000 0.0338
-14.500 -0.8708 0.04989 0.04375 -0.0898 1.0000 0.0343
-14.250 -0.8762 0.04744 0.04119 -0.0893 1.0000 0.0347
-14.000 -0.8816 0.04519 0.03882 -0.0885 1.0000 0.0351
-13.750 -0.8870 0.04311 0.03663 -0.0874 1.0000 0.0356
-13.500 -0.8921 0.04124 0.03464 -0.0858 1.0000 0.0360
-13.250 -0.8978 0.03953 0.03280 -0.0838 1.0000 0.0364
-13.000 -0.9036 0.03801 0.03115 -0.0815 1.0000 0.0368
-12.750 -0.9085 0.03664 0.02973 -0.0787 1.0000 0.0372
-12.500 -0.9068 0.03532 0.02839 -0.0769 0.9993 0.0376
-12.250 -0.8865 0.03377 0.02680 -0.0785 0.9955 0.0385
-12.000 -0.8667 0.03236 0.02532 -0.0798 0.9911 0.0393
-11.750 -0.8462 0.03105 0.02392 -0.0810 0.9862 0.0403
-11.500 -0.8225 0.02982 0.02258 -0.0824 0.9825 0.0412
-11.250 -0.8042 0.02872 0.02136 -0.0825 0.9762 0.0421
-11.000 -0.7805 0.02765 0.02016 -0.0835 0.9719 0.0429
-10.750 -0.7638 0.02651 0.01902 -0.0832 0.9652 0.0439
-10.250 -0.7188 0.02463 0.01704 -0.0839 0.9549 0.0463
-10.000 -0.7008 0.02384 0.01616 -0.0830 0.9471 0.0475
-9.750 -0.6727 0.02296 0.01518 -0.0841 0.9434 0.0487
-9.500 -0.6560 0.02220 0.01438 -0.0828 0.9346 0.0500
-9.250 -0.6319 0.02139 0.01354 -0.0831 0.9292 0.0519
-9.000 -0.6124 0.02076 0.01286 -0.0821 0.9216 0.0539
-8.750 -0.5900 0.02014 0.01216 -0.0816 0.9148 0.0564
-8.500 -0.5676 0.01949 0.01152 -0.0812 0.9085 0.0591
-8.250 -0.5477 0.01897 0.01096 -0.0801 0.9005 0.0630
-8.000 -0.5203 0.01838 0.01040 -0.0805 0.8963 0.0696
-7.750 -0.5004 0.01799 0.01004 -0.0793 0.8882 0.0780
-7.500 -0.4726 0.01759 0.00961 -0.0796 0.8832 0.0890
-7.250 -0.4444 0.01723 0.00919 -0.0799 0.8786 0.0983
-7.000 -0.4208 0.01695 0.00884 -0.0793 0.8720 0.1056
-6.750 -0.3936 0.01653 0.00837 -0.0794 0.8673 0.1119
-6.500 -0.3670 0.01617 0.00795 -0.0794 0.8624 0.1182
-6.250 -0.3438 0.01589 0.00761 -0.0787 0.8563 0.1237
-6.000 -0.3178 0.01548 0.00719 -0.0786 0.8516 0.1307
-5.750 -0.2907 0.01515 0.00681 -0.0786 0.8472 0.1383
-5.500 -0.2701 0.01482 0.00653 -0.0774 0.8410 0.1490
-5.250 -0.2461 0.01443 0.00620 -0.0769 0.8362 0.1665
-5.000 -0.2206 0.01395 0.00588 -0.0768 0.8322 0.2049
-4.750 -0.2013 0.01366 0.00574 -0.0753 0.8262 0.2461
-4.500 -0.1781 0.01341 0.00557 -0.0746 0.8212 0.2803
-4.250 -0.1523 0.01315 0.00537 -0.0743 0.8171 0.3085
-4.000 -0.1280 0.01297 0.00523 -0.0736 0.8125 0.3300
-3.750 -0.1057 0.01284 0.00514 -0.0726 0.8072 0.3496
-3.500 -0.0814 0.01268 0.00504 -0.0719 0.8026 0.3728
-3.250 -0.0545 0.01254 0.00496 -0.0717 0.7988 0.4013
-3.000 -0.0317 0.01249 0.00496 -0.0707 0.7939 0.4237
-2.750 -0.0081 0.01246 0.00495 -0.0698 0.7888 0.4449
-2.500 0.0182 0.01241 0.00489 -0.0694 0.7841 0.4643
-2.250 0.0457 0.01236 0.00481 -0.0693 0.7791 0.4818
-2.000 0.0674 0.01233 0.00480 -0.0679 0.7718 0.4955
-1.750 0.0940 0.01228 0.00471 -0.0676 0.7658 0.5079
-1.500 0.1201 0.01223 0.00465 -0.0671 0.7603 0.5200
-1.250 0.1427 0.01218 0.00464 -0.0660 0.7532 0.5312
-1.000 0.1694 0.01212 0.00457 -0.0656 0.7477 0.5427
-0.750 0.1944 0.01207 0.00455 -0.0649 0.7422 0.5550
-0.500 0.2169 0.01201 0.00455 -0.0638 0.7350 0.5687
-0.250 0.2434 0.01193 0.00449 -0.0633 0.7292 0.5835
0.000 0.2659 0.01189 0.00452 -0.0622 0.7222 0.5980
0.250 0.2898 0.01183 0.00450 -0.0612 0.7150 0.6133
0.750 0.3365 0.01171 0.00452 -0.0591 0.6998 0.6504
1.000 0.3610 0.01163 0.00449 -0.0582 0.6917 0.6712
1.250 0.3828 0.01157 0.00451 -0.0568 0.6819 0.6933
1.500 0.4065 0.01151 0.00453 -0.0558 0.6735 0.7171
1.750 0.4295 0.01146 0.00458 -0.0546 0.6645 0.7437
2.000 0.4534 0.01141 0.00464 -0.0535 0.6552 0.7734
2.250 0.4802 0.01138 0.00470 -0.0530 0.6446 0.8050
2.500 0.5091 0.01142 0.00483 -0.0530 0.6330 0.8377
2.750 0.5421 0.01149 0.00495 -0.0539 0.6200 0.8670
3.000 0.5783 0.01161 0.00506 -0.0555 0.6039 0.8891
3.250 0.6144 0.01176 0.00518 -0.0571 0.5854 0.9078
3.500 0.6497 0.01195 0.00531 -0.0587 0.5644 0.9247
3.750 0.6825 0.01218 0.00545 -0.0597 0.5389 0.9401
4.000 0.7127 0.01250 0.00563 -0.0603 0.5073 0.9541
4.250 0.7416 0.01291 0.00586 -0.0608 0.4684 0.9663
4.500 0.7676 0.01343 0.00616 -0.0609 0.4284 0.9790
4.750 0.7936 0.01402 0.00653 -0.0611 0.3909 0.9909
5.000 0.8189 0.01460 0.00693 -0.0613 0.3633 1.0000
5.250 0.8191 0.01490 0.00713 -0.0561 0.3494 1.0000
5.500 0.8207 0.01521 0.00735 -0.0512 0.3378 1.0000
5.750 0.8259 0.01554 0.00760 -0.0470 0.3273 1.0000
6.000 0.8345 0.01586 0.00788 -0.0435 0.3178 1.0000
6.250 0.8440 0.01623 0.00819 -0.0403 0.3095 1.0000
6.500 0.8561 0.01657 0.00851 -0.0376 0.3018 1.0000
6.750 0.8686 0.01693 0.00885 -0.0349 0.2942 1.0000
7.000 0.8812 0.01733 0.00921 -0.0324 0.2867 1.0000
7.250 0.8959 0.01767 0.00957 -0.0303 0.2795 1.0000
7.500 0.9092 0.01811 0.00998 -0.0280 0.2733 1.0000
7.750 0.9254 0.01846 0.01036 -0.0262 0.2677 1.0000
8.000 0.9410 0.01884 0.01077 -0.0243 0.2612 1.0000
8.250 0.9542 0.01933 0.01123 -0.0222 0.2539 1.0000
8.500 0.9704 0.01972 0.01168 -0.0205 0.2463 1.0000
8.750 0.9838 0.02023 0.01218 -0.0186 0.2393 1.0000
9.000 0.9997 0.02067 0.01267 -0.0170 0.2310 1.0000
9.250 1.0122 0.02126 0.01324 -0.0150 0.2224 1.0000
9.500 1.0277 0.02176 0.01379 -0.0135 0.2129 1.0000
9.750 1.0394 0.02243 0.01444 -0.0115 0.1984 1.0000
10.000 1.0504 0.02319 0.01516 -0.0096 0.1821 1.0000
10.250 1.0586 0.02415 0.01602 -0.0076 0.1599 1.0000
10.500 1.0626 0.02545 0.01712 -0.0052 0.1259 1.0000
10.750 1.0535 0.02772 0.01897 -0.0018 0.0740 1.0000
11.000 1.0559 0.02933 0.02048 0.0004 0.0573 1.0000
11.250 1.0620 0.03072 0.02185 0.0021 0.0503 1.0000
11.500 1.0704 0.03197 0.02313 0.0036 0.0472 1.0000
11.750 1.0771 0.03337 0.02457 0.0051 0.0447 1.0000
12.000 1.0838 0.03481 0.02607 0.0065 0.0432 1.0000
12.250 1.0908 0.03625 0.02760 0.0078 0.0419 1.0000
12.500 1.0969 0.03781 0.02925 0.0090 0.0410 1.0000
12.750 1.1017 0.03952 0.03104 0.0102 0.0398 1.0000
13.000 1.1046 0.04145 0.03305 0.0113 0.0389 1.0000
13.250 1.1061 0.04357 0.03524 0.0123 0.0383 1.0000
13.500 1.1046 0.04605 0.03779 0.0132 0.0375 1.0000
13.750 1.1071 0.04824 0.04009 0.0138 0.0370 1.0000
14.000 1.1087 0.05060 0.04255 0.0143 0.0364 1.0000
14.250 1.1091 0.05315 0.04520 0.0147 0.0360 1.0000
14.500 1.1087 0.05588 0.04803 0.0150 0.0354 1.0000
14.750 1.1084 0.05869 0.05093 0.0151 0.0351 1.0000
15.000 1.1072 0.06166 0.05398 0.0151 0.0345 1.0000
15.250 1.1061 0.06469 0.05710 0.0149 0.0342 1.0000
15.500 1.1049 0.06780 0.06029 0.0147 0.0338 1.0000
15.750 1.1035 0.07099 0.06354 0.0143 0.0333 1.0000
16.000 1.1019 0.07422 0.06683 0.0139 0.0328 1.0000
16.250 1.1011 0.07732 0.06996 0.0135 0.0324 1.0000
16.500 1.1017 0.08024 0.07291 0.0132 0.0319 1.0000
16.750 1.1039 0.08310 0.07587 0.0127 0.0316 1.0000
17.000 1.1061 0.08598 0.07885 0.0122 0.0312 1.0000
17.250 1.1081 0.08892 0.08189 0.0116 0.0308 1.0000
17.500 1.1107 0.09173 0.08479 0.0110 0.0304 1.0000
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