GOE 570 AIRFOIL (goe570-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 570 AIRFOIL (goe570-il) Reynolds number: 500,000 Max Cl/Cd: 15.77 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe570-il-500000-n5.txt Download as CSV file: xf-goe570-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 570 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 0.0330 0.06880 0.06273 -0.2237 0.7189 0.0507
-19.500 0.0316 0.06629 0.06016 -0.2248 0.7159 0.0507
-19.250 0.0325 0.06407 0.05789 -0.2258 0.7125 0.0508
-19.000 0.0334 0.06185 0.05563 -0.2269 0.7089 0.0513
-18.750 0.0338 0.05975 0.05345 -0.2275 0.7053 0.0513
-18.500 0.0346 0.05777 0.05138 -0.2281 0.7011 0.0514
-18.250 0.0363 0.05583 0.04938 -0.2288 0.6979 0.0517
-18.000 0.0375 0.05389 0.04739 -0.2293 0.6952 0.0520
-17.750 0.0409 0.05218 0.04565 -0.2297 0.6925 0.0520
-17.500 0.0433 0.05051 0.04393 -0.2298 0.6891 0.0519
-17.250 0.0458 0.04882 0.04218 -0.2302 0.6859 0.0523
-17.000 0.0481 0.04724 0.04054 -0.2301 0.6823 0.0524
-16.750 0.0514 0.04586 0.03909 -0.2299 0.6788 0.0524
-16.500 0.0535 0.04434 0.03751 -0.2298 0.6754 0.0527
-16.250 0.0570 0.04292 0.03606 -0.2296 0.6727 0.0528
-16.000 0.0600 0.04155 0.03466 -0.2292 0.6696 0.0530
-15.750 0.0628 0.04025 0.03332 -0.2287 0.6663 0.0530
-15.500 0.0650 0.03898 0.03198 -0.2280 0.6625 0.0533
-15.250 0.0669 0.03778 0.03072 -0.2271 0.6590 0.0535
-15.000 0.0685 0.03665 0.02952 -0.2260 0.6554 0.0535
-14.750 0.0714 0.03546 0.02831 -0.2252 0.6525 0.0538
-14.500 0.0726 0.03434 0.02715 -0.2239 0.6485 0.0539
-14.250 0.0737 0.03328 0.02605 -0.2225 0.6447 0.0541
-14.000 0.0737 0.03227 0.02499 -0.2208 0.6408 0.0540
-13.750 0.0724 0.03129 0.02394 -0.2188 0.6371 0.0543
-13.500 0.0721 0.03032 0.02293 -0.2169 0.6335 0.0543
-13.250 0.0720 0.02942 0.02200 -0.2148 0.6298 0.0545
-13.000 0.0664 0.02854 0.02108 -0.2117 0.6246 0.0545
-12.750 0.0612 0.02774 0.02022 -0.2086 0.6202 0.0546
-12.500 0.0563 0.02704 0.01945 -0.2053 0.6161 0.0547
-12.250 0.0544 0.02628 0.01865 -0.2025 0.6124 0.0549
-12.000 0.0514 0.02560 0.01795 -0.1993 0.6081 0.0549
-11.750 0.0429 0.02489 0.01720 -0.1953 0.6036 0.0552
-11.500 0.0315 0.02424 0.01649 -0.1906 0.5990 0.0554
-11.250 0.0215 0.02372 0.01593 -0.1858 0.5949 0.0556
-11.000 0.0147 0.02326 0.01544 -0.1813 0.5904 0.0556
-10.750 0.0035 0.02281 0.01496 -0.1760 0.5852 0.0558
-10.500 -0.0083 0.02249 0.01458 -0.1703 0.5801 0.0559
-10.250 -0.0191 0.02221 0.01425 -0.1647 0.5760 0.0561
-10.000 -0.0283 0.02190 0.01393 -0.1592 0.5718 0.0563
-9.750 -0.0361 0.02169 0.01368 -0.1538 0.5674 0.0565
-9.500 -0.0484 0.02155 0.01349 -0.1475 0.5628 0.0567
-9.250 -0.0587 0.02146 0.01334 -0.1414 0.5588 0.0567
-9.000 -0.0651 0.02129 0.01316 -0.1360 0.5550 0.0571
-8.750 -0.0727 0.02120 0.01304 -0.1303 0.5507 0.0573
-8.500 -0.0816 0.02117 0.01297 -0.1243 0.5461 0.0573
-8.250 -0.0915 0.02120 0.01293 -0.1181 0.5419 0.0576
-8.000 -0.0978 0.02118 0.01288 -0.1125 0.5383 0.0578
-7.750 -0.1027 0.02116 0.01284 -0.1071 0.5350 0.0580
-7.500 -0.1055 0.02116 0.01281 -0.1021 0.5314 0.0584
-7.250 -0.1084 0.02121 0.01282 -0.0970 0.5277 0.0586
-7.000 -0.1122 0.02130 0.01286 -0.0918 0.5242 0.0589
-6.750 -0.1144 0.02139 0.01290 -0.0869 0.5205 0.0592
-6.500 -0.1116 0.02142 0.01291 -0.0828 0.5176 0.0598
-6.250 -0.1101 0.02148 0.01295 -0.0785 0.5147 0.0600
-6.000 -0.1097 0.02160 0.01303 -0.0740 0.5104 0.0601
-5.750 -0.1079 0.02172 0.01311 -0.0698 0.5071 0.0606
-5.500 -0.1075 0.02191 0.01325 -0.0654 0.5038 0.0611
-5.250 -0.1046 0.02201 0.01331 -0.0613 0.5009 0.0615
-5.000 -0.0974 0.02208 0.01338 -0.0581 0.4985 0.0617
-4.750 -0.0918 0.02217 0.01347 -0.0546 0.4957 0.0626
-4.500 -0.0860 0.02231 0.01361 -0.0512 0.4927 0.0634
-4.250 -0.0789 0.02247 0.01374 -0.0480 0.4897 0.0641
-4.000 -0.0724 0.02267 0.01390 -0.0448 0.4861 0.0654
-3.750 -0.0662 0.02294 0.01412 -0.0417 0.4827 0.0658
-3.500 -0.0542 0.02310 0.01428 -0.0394 0.4805 0.0667
-3.250 -0.0415 0.02327 0.01446 -0.0374 0.4780 0.0681
-3.000 -0.0289 0.02345 0.01465 -0.0354 0.4752 0.0696
-2.750 -0.0169 0.02369 0.01489 -0.0334 0.4725 0.0719
-2.500 -0.0038 0.02394 0.01513 -0.0316 0.4697 0.0749
-2.250 0.0099 0.02419 0.01537 -0.0299 0.4669 0.0777
-1.750 0.0397 0.02474 0.01595 -0.0271 0.4615 0.0879
-1.500 0.0563 0.02500 0.01625 -0.0261 0.4590 0.0945
-1.250 0.0730 0.02528 0.01655 -0.0251 0.4561 0.1021
-1.000 0.0895 0.02559 0.01687 -0.0242 0.4535 0.1091
-0.750 0.1055 0.02590 0.01725 -0.0233 0.4506 0.1236
-0.500 0.1235 0.02613 0.01770 -0.0229 0.4481 0.1720
-0.250 0.1400 0.02652 0.01808 -0.0219 0.4455 0.1809
0.000 0.1575 0.02692 0.01851 -0.0213 0.4433 0.1878
0.250 0.1743 0.02737 0.01898 -0.0205 0.4410 0.1948
0.500 0.1894 0.02790 0.01951 -0.0195 0.4383 0.1977
0.750 0.2052 0.02840 0.02001 -0.0186 0.4354 0.2028
1.000 0.2220 0.02886 0.02047 -0.0180 0.4330 0.2073
1.250 0.2383 0.02936 0.02095 -0.0172 0.4305 0.2115
1.500 0.2538 0.02990 0.02146 -0.0164 0.4280 0.2154
1.750 0.2704 0.03045 0.02202 -0.0158 0.4261 0.2179
2.000 0.2876 0.03097 0.02257 -0.0153 0.4240 0.2222
2.250 0.3047 0.03149 0.02314 -0.0148 0.4216 0.2281
2.500 0.3201 0.03212 0.02377 -0.0142 0.4188 0.2331
3.000 0.3509 0.03337 0.02507 -0.0131 0.4140 0.2497
3.500 0.3880 0.03429 0.02637 -0.0132 0.4094 0.3525
3.750 0.4056 0.03479 0.02711 -0.0130 0.4077 0.4087
4.000 0.4193 0.03555 0.02799 -0.0124 0.4054 0.4362
4.250 0.4337 0.03629 0.02881 -0.0118 0.4032 0.4579
4.500 0.4481 0.03702 0.02961 -0.0113 0.4006 0.4800
4.750 0.4624 0.03772 0.03038 -0.0107 0.3980 0.5010
5.000 0.4765 0.03845 0.03115 -0.0101 0.3956 0.5180
5.250 0.4914 0.03914 0.03189 -0.0096 0.3937 0.5394
5.500 0.5048 0.03997 0.03281 -0.0090 0.3918 0.5601
5.750 0.5185 0.04076 0.03371 -0.0084 0.3900 0.5825
6.000 0.5315 0.04156 0.03462 -0.0077 0.3879 0.6068
6.250 0.5415 0.04232 0.03560 -0.0065 0.3857 0.6539
6.500 0.7364 0.04671 0.04099 -0.0444 0.3824 0.9359
6.750 0.7347 0.04763 0.04189 -0.0408 0.3803 0.9497
7.000 0.7411 0.04880 0.04301 -0.0391 0.3777 0.9581
7.250 0.7584 0.04994 0.04413 -0.0394 0.3759 0.9645
7.500 0.7646 0.05120 0.04542 -0.0376 0.3742 0.9703
7.750 0.7840 0.05259 0.04682 -0.0387 0.3724 0.9732
8.000 0.8069 0.05430 0.04854 -0.0411 0.3700 0.9753
8.250 0.8268 0.05575 0.04999 -0.0426 0.3679 0.9770
8.500 0.8458 0.05709 0.05132 -0.0439 0.3657 0.9787
8.750 0.8643 0.05839 0.05258 -0.0449 0.3637 0.9803
9.000 0.8846 0.05974 0.05390 -0.0464 0.3617 0.9825
9.250 0.9027 0.06097 0.05511 -0.0473 0.3597 0.9841
9.500 0.9148 0.06280 0.05699 -0.0478 0.3580 0.9859
9.750 0.9252 0.06462 0.05884 -0.0480 0.3556 0.9874
10.000 0.9335 0.06644 0.06068 -0.0477 0.3534 0.9886
10.250 0.9462 0.06825 0.06251 -0.0484 0.3510 0.9898
10.500 0.9702 0.06990 0.06415 -0.0512 0.3491 0.9919
10.750 0.9917 0.07136 0.06560 -0.0533 0.3472 0.9938
11.000 1.0176 0.07282 0.06702 -0.0562 0.3454 0.9962
11.250 1.0536 0.07432 0.06851 -0.0610 0.3436 0.9992
11.500 1.0595 0.07690 0.07117 -0.0616 0.3417 1.0000
11.750 1.0623 0.07878 0.07309 -0.0607 0.3399 1.0000
12.000 1.0648 0.08070 0.07505 -0.0599 0.3378 1.0000
12.250 1.0658 0.08277 0.07715 -0.0589 0.3356 1.0000
12.500 1.0724 0.08430 0.07868 -0.0584 0.3337 1.0000
12.750 1.0814 0.08561 0.07997 -0.0580 0.3318 1.0000
13.000 1.0926 0.08668 0.08103 -0.0579 0.3303 1.0000
13.250 1.1077 0.08736 0.08166 -0.0579 0.3284 1.0000
13.500 1.0987 0.09044 0.08483 -0.0565 0.3262 1.0000
13.750 1.0960 0.09292 0.08738 -0.0555 0.3243 1.0000
14.000 1.0862 0.09612 0.09066 -0.0542 0.3214 1.0000
14.250 1.0885 0.09813 0.09269 -0.0536 0.3194 1.0000
14.500 1.0965 0.09956 0.09412 -0.0534 0.3177 1.0000
14.750 1.1065 0.10076 0.09531 -0.0533 0.3163 1.0000
15.000 1.1187 0.10173 0.09627 -0.0534 0.3150 1.0000
15.250 1.1337 0.10240 0.09691 -0.0536 0.3138 1.0000
15.500 1.1453 0.10341 0.09792 -0.0537 0.3124 1.0000
15.750 1.1020 0.11016 0.10488 -0.0507 0.3084 1.0000
16.000 1.0878 0.11394 0.10873 -0.0494 0.3052 1.0000
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