GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 620 AIRFOIL (goe620-il) Reynolds number: 200,000 Max Cl/Cd: 64.72 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe620-il-200000-n5.txt Download as CSV file: xf-goe620-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 620 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.0928 0.10498 0.10070 -0.1053 0.9397 0.0433
-12.250 -0.3786 0.04444 0.03914 -0.1538 0.9222 0.0454
-12.000 -0.3914 0.03850 0.03281 -0.1622 0.9078 0.0456
-11.750 -0.3983 0.03544 0.02943 -0.1643 0.8948 0.0459
-11.500 -0.3980 0.03334 0.02703 -0.1641 0.8853 0.0462
-11.250 -0.3996 0.03184 0.02526 -0.1620 0.8738 0.0466
-11.000 -0.3834 0.03038 0.02362 -0.1620 0.8673 0.0470
-10.750 -0.3722 0.02942 0.02262 -0.1604 0.8584 0.0474
-10.500 -0.3538 0.02846 0.02156 -0.1600 0.8521 0.0479
-10.250 -0.3374 0.02759 0.02059 -0.1590 0.8460 0.0485
-10.000 -0.3226 0.02680 0.01970 -0.1577 0.8388 0.0491
-9.750 -0.3036 0.02593 0.01867 -0.1570 0.8333 0.0500
-9.500 -0.2861 0.02511 0.01770 -0.1559 0.8276 0.0507
-9.250 -0.2695 0.02437 0.01681 -0.1545 0.8215 0.0513
-9.000 -0.2490 0.02360 0.01586 -0.1537 0.8164 0.0520
-8.750 -0.2263 0.02286 0.01497 -0.1533 0.8120 0.0527
-8.500 -0.2087 0.02222 0.01434 -0.1518 0.8060 0.0533
-8.250 -0.1880 0.02163 0.01372 -0.1508 0.8006 0.0540
-8.000 -0.1642 0.02106 0.01309 -0.1504 0.7961 0.0550
-7.750 -0.1430 0.02057 0.01253 -0.1494 0.7911 0.0561
-7.500 -0.1229 0.02012 0.01200 -0.1482 0.7855 0.0572
-7.250 -0.1000 0.01966 0.01143 -0.1474 0.7808 0.0583
-7.000 -0.0756 0.01913 0.01083 -0.1469 0.7769 0.0594
-6.750 -0.0549 0.01869 0.01039 -0.1458 0.7722 0.0605
-6.500 -0.0341 0.01832 0.01001 -0.1446 0.7672 0.0616
-6.250 -0.0110 0.01795 0.00959 -0.1438 0.7627 0.0631
-6.000 0.0146 0.01761 0.00915 -0.1434 0.7589 0.0650
-5.750 0.0377 0.01726 0.00877 -0.1426 0.7547 0.0667
-5.500 0.0585 0.01696 0.00849 -0.1413 0.7497 0.0687
-5.250 0.0819 0.01669 0.00817 -0.1405 0.7451 0.0709
-5.000 0.1076 0.01642 0.00783 -0.1400 0.7411 0.0735
-4.750 0.1337 0.01613 0.00752 -0.1397 0.7374 0.0770
-4.500 0.1547 0.01594 0.00734 -0.1384 0.7322 0.0816
-4.250 0.1779 0.01570 0.00712 -0.1374 0.7274 0.0878
-4.000 0.2033 0.01546 0.00687 -0.1369 0.7231 0.0974
-3.750 0.2313 0.01522 0.00660 -0.1369 0.7195 0.1117
-3.500 0.2517 0.01503 0.00651 -0.1355 0.7142 0.1277
-3.250 0.2745 0.01485 0.00641 -0.1345 0.7090 0.1472
-3.000 0.3003 0.01471 0.00628 -0.1340 0.7045 0.1671
-2.750 0.3292 0.01460 0.00613 -0.1341 0.7006 0.1857
-2.500 0.3495 0.01454 0.00615 -0.1326 0.6948 0.2011
-2.250 0.3729 0.01446 0.00610 -0.1317 0.6894 0.2162
-2.000 0.3993 0.01438 0.00601 -0.1313 0.6847 0.2322
-1.750 0.4249 0.01432 0.00596 -0.1307 0.6800 0.2474
-1.500 0.4460 0.01429 0.00597 -0.1293 0.6737 0.2615
-1.250 0.4704 0.01424 0.00593 -0.1285 0.6682 0.2770
-1.000 0.4981 0.01417 0.00585 -0.1284 0.6637 0.2950
-0.750 0.5173 0.01415 0.00592 -0.1266 0.6569 0.3109
-0.500 0.5405 0.01411 0.00591 -0.1256 0.6507 0.3270
-0.250 0.5672 0.01406 0.00583 -0.1252 0.6457 0.3446
0.000 0.5864 0.01407 0.00591 -0.1235 0.6385 0.3606
0.250 0.6092 0.01404 0.00590 -0.1224 0.6320 0.3798
0.500 0.6330 0.01400 0.00589 -0.1215 0.6261 0.4010
0.750 0.6521 0.01400 0.00597 -0.1197 0.6185 0.4212
1.000 0.6751 0.01396 0.00595 -0.1186 0.6119 0.4427
1.250 0.6940 0.01396 0.00601 -0.1167 0.6039 0.4646
1.500 0.7141 0.01394 0.00603 -0.1151 0.5956 0.4897
1.750 0.7314 0.01394 0.00608 -0.1129 0.5861 0.5186
2.000 0.7488 0.01391 0.00607 -0.1107 0.5762 0.5514
2.250 0.7629 0.01392 0.00616 -0.1079 0.5658 0.5861
2.500 0.7803 0.01391 0.00620 -0.1057 0.5564 0.6275
2.750 0.7965 0.01390 0.00637 -0.1034 0.5473 0.6873
3.250 0.9111 0.01411 0.00688 -0.1159 0.5256 1.0000
3.500 0.9267 0.01433 0.00703 -0.1135 0.5172 1.0000
3.750 0.9425 0.01457 0.00718 -0.1113 0.5085 1.0000
4.000 0.9591 0.01482 0.00736 -0.1092 0.5009 1.0000
4.250 0.9754 0.01508 0.00757 -0.1071 0.4928 1.0000
4.500 0.9925 0.01537 0.00777 -0.1052 0.4856 1.0000
4.750 1.0090 0.01565 0.00804 -0.1032 0.4780 1.0000
5.000 1.0257 0.01596 0.00828 -0.1013 0.4708 1.0000
5.250 1.0420 0.01629 0.00858 -0.0994 0.4633 1.0000
5.500 1.0580 0.01663 0.00889 -0.0975 0.4555 1.0000
5.750 1.0735 0.01701 0.00921 -0.0955 0.4479 1.0000
6.000 1.0891 0.01739 0.00958 -0.0936 0.4398 1.0000
6.250 1.1041 0.01782 0.00995 -0.0917 0.4325 1.0000
6.500 1.1198 0.01824 0.01037 -0.0899 0.4247 1.0000
6.750 1.1341 0.01872 0.01081 -0.0879 0.4169 1.0000
7.000 1.1491 0.01920 0.01129 -0.0862 0.4095 1.0000
7.250 1.1622 0.01976 0.01181 -0.0842 0.4005 1.0000
7.500 1.1754 0.02035 0.01237 -0.0822 0.3918 1.0000
7.750 1.1873 0.02100 0.01299 -0.0802 0.3824 1.0000
8.000 1.2001 0.02166 0.01364 -0.0784 0.3736 1.0000
8.250 1.2123 0.02237 0.01433 -0.0765 0.3654 1.0000
8.500 1.2250 0.02309 0.01504 -0.0748 0.3573 1.0000
8.750 1.2366 0.02388 0.01582 -0.0731 0.3490 1.0000
9.000 1.2491 0.02467 0.01660 -0.0715 0.3419 1.0000
9.250 1.2610 0.02551 0.01744 -0.0698 0.3341 1.0000
9.500 1.2719 0.02643 0.01834 -0.0682 0.3271 1.0000
9.750 1.2839 0.02732 0.01925 -0.0667 0.3197 1.0000
10.000 1.2937 0.02835 0.02026 -0.0651 0.3130 1.0000
10.250 1.3055 0.02932 0.02124 -0.0638 0.3059 1.0000
10.500 1.3152 0.03042 0.02234 -0.0623 0.2989 1.0000
10.750 1.3253 0.03153 0.02346 -0.0609 0.2928 1.0000
11.000 1.3362 0.03262 0.02458 -0.0596 0.2863 1.0000
11.250 1.3453 0.03385 0.02580 -0.0582 0.2809 1.0000
11.500 1.3565 0.03496 0.02694 -0.0571 0.2762 1.0000
11.750 1.3675 0.03612 0.02815 -0.0560 0.2709 1.0000
12.000 1.3769 0.03740 0.02945 -0.0548 0.2660 1.0000
12.250 1.3851 0.03879 0.03084 -0.0536 0.2613 1.0000
12.500 1.3953 0.04008 0.03220 -0.0526 0.2556 1.0000
12.750 1.4033 0.04155 0.03369 -0.0516 0.2503 1.0000
13.000 1.4098 0.04315 0.03529 -0.0504 0.2456 1.0000
13.250 1.4198 0.04452 0.03675 -0.0496 0.2410 1.0000
13.500 1.4275 0.04611 0.03840 -0.0487 0.2358 1.0000
13.750 1.4334 0.04786 0.04017 -0.0477 0.2309 1.0000
14.000 1.4394 0.04963 0.04200 -0.0468 0.2258 1.0000
14.250 1.4459 0.05143 0.04386 -0.0461 0.2200 1.0000
14.500 1.4489 0.05355 0.04601 -0.0452 0.2143 1.0000
14.750 1.4536 0.05556 0.04808 -0.0445 0.2087 1.0000
15.000 1.4573 0.05773 0.05033 -0.0439 0.2022 1.0000
15.250 1.4573 0.06028 0.05289 -0.0432 0.1963 1.0000
15.500 1.4614 0.06248 0.05520 -0.0427 0.1890 1.0000
15.750 1.4593 0.06538 0.05811 -0.0422 0.1819 1.0000
16.000 1.4595 0.06810 0.06089 -0.0418 0.1732 1.0000
16.250 1.4568 0.07116 0.06398 -0.0415 0.1660 1.0000
16.500 1.4522 0.07450 0.06733 -0.0413 0.1580 1.0000
16.750 1.4473 0.07791 0.07076 -0.0412 0.1521 1.0000
17.000 1.4414 0.08150 0.07436 -0.0411 0.1466 1.0000
17.250 1.4360 0.08505 0.07792 -0.0412 0.1423 1.0000
17.500 1.4328 0.08836 0.08127 -0.0413 0.1384 1.0000
17.750 1.4297 0.09165 0.08460 -0.0414 0.1354 1.0000
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Polar data table (+)
Polar graphs
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