GOE 626 AIRFOIL (goe626-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 626 AIRFOIL (goe626-il) Reynolds number: 500,000 Max Cl/Cd: 90.44 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe626-il-500000.txt Download as CSV file: xf-goe626-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 626 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.7240 0.09955 0.09598 -0.0709 1.0000 0.0333
-17.000 -0.7360 0.09437 0.09072 -0.0736 1.0000 0.0335
-16.750 -0.7510 0.08885 0.08508 -0.0766 1.0000 0.0335
-16.500 -0.7618 0.08421 0.08035 -0.0789 1.0000 0.0336
-16.250 -0.7669 0.08059 0.07667 -0.0804 1.0000 0.0339
-16.000 -0.7715 0.07717 0.07319 -0.0818 1.0000 0.0340
-15.750 -0.7759 0.07390 0.06986 -0.0830 1.0000 0.0342
-15.500 -0.7799 0.07084 0.06673 -0.0839 1.0000 0.0343
-15.250 -0.7835 0.06797 0.06381 -0.0846 1.0000 0.0344
-15.000 -0.7866 0.06533 0.06112 -0.0851 1.0000 0.0346
-14.750 -0.7896 0.06290 0.05865 -0.0852 1.0000 0.0348
-14.500 -0.7936 0.06060 0.05631 -0.0851 1.0000 0.0349
-14.250 -0.7993 0.05842 0.05409 -0.0846 1.0000 0.0350
-14.000 -0.8060 0.05642 0.05205 -0.0837 1.0000 0.0352
-13.750 -0.8149 0.05455 0.05016 -0.0824 1.0000 0.0353
-13.500 -0.8272 0.05273 0.04833 -0.0806 1.0000 0.0354
-13.250 -0.8236 0.05030 0.04584 -0.0825 0.9987 0.0356
-13.000 -0.8061 0.04781 0.04328 -0.0864 0.9959 0.0359
-12.750 -0.7887 0.04499 0.04038 -0.0913 0.9929 0.0362
-12.500 -0.7742 0.04255 0.03787 -0.0948 0.9885 0.0364
-12.250 -0.7560 0.04018 0.03543 -0.0988 0.9840 0.0366
-12.000 -0.7327 0.03859 0.03384 -0.1020 0.9810 0.0369
-11.750 -0.7174 0.03671 0.03196 -0.1042 0.9741 0.0373
-11.500 -0.6931 0.03428 0.02952 -0.1092 0.9700 0.0378
-11.250 -0.6639 0.03154 0.02675 -0.1156 0.9677 0.0381
-11.000 -0.6453 0.02870 0.02384 -0.1200 0.9607 0.0385
-10.750 -0.6152 0.02582 0.02087 -0.1259 0.9570 0.0390
-10.500 -0.5806 0.02325 0.01819 -0.1315 0.9550 0.0397
-10.250 -0.5451 0.02159 0.01644 -0.1356 0.9535 0.0403
-10.000 -0.5079 0.02024 0.01499 -0.1394 0.9524 0.0410
-9.750 -0.4867 0.01930 0.01397 -0.1394 0.9457 0.0414
-9.500 -0.4554 0.01795 0.01256 -0.1418 0.9424 0.0422
-9.250 -0.4221 0.01684 0.01138 -0.1441 0.9400 0.0432
-9.000 -0.3871 0.01593 0.01041 -0.1463 0.9379 0.0443
-8.750 -0.3571 0.01523 0.00964 -0.1472 0.9340 0.0454
-8.500 -0.3313 0.01466 0.00900 -0.1471 0.9279 0.0466
-8.250 -0.2991 0.01391 0.00820 -0.1484 0.9236 0.0491
-8.000 -0.2643 0.01318 0.00746 -0.1501 0.9197 0.0546
-7.750 -0.2417 0.01253 0.00689 -0.1493 0.9114 0.0712
-7.500 -0.2118 0.01189 0.00627 -0.1499 0.9055 0.0900
-7.250 -0.1820 0.01126 0.00569 -0.1506 0.9000 0.1093
-7.000 -0.1572 0.01070 0.00521 -0.1501 0.8921 0.1338
-6.750 -0.1271 0.01021 0.00478 -0.1507 0.8859 0.1620
-6.500 -0.1001 0.00994 0.00458 -0.1504 0.8782 0.1834
-6.250 -0.0714 0.00981 0.00446 -0.1503 0.8703 0.2002
-6.000 -0.0416 0.00977 0.00440 -0.1503 0.8626 0.2128
-5.750 -0.0139 0.00974 0.00431 -0.1499 0.8532 0.2213
-5.500 0.0158 0.00978 0.00432 -0.1498 0.8444 0.2285
-5.250 0.0436 0.00981 0.00426 -0.1494 0.8334 0.2344
-5.000 0.0717 0.00981 0.00422 -0.1491 0.8225 0.2390
-4.750 0.1002 0.00991 0.00426 -0.1488 0.8103 0.2437
-4.500 0.1273 0.00997 0.00426 -0.1482 0.7959 0.2479
-4.250 0.1546 0.01006 0.00422 -0.1476 0.7800 0.2513
-4.000 0.1812 0.01004 0.00415 -0.1470 0.7617 0.2550
-3.750 0.2074 0.01016 0.00419 -0.1463 0.7402 0.2583
-3.250 0.2585 0.01054 0.00431 -0.1446 0.6924 0.2659
-3.000 0.2842 0.01074 0.00434 -0.1438 0.6731 0.2684
-2.750 0.3096 0.01072 0.00423 -0.1431 0.6574 0.2718
-2.500 0.3356 0.01089 0.00436 -0.1424 0.6436 0.2751
-2.250 0.3623 0.01105 0.00447 -0.1419 0.6318 0.2784
-2.000 0.3887 0.01117 0.00450 -0.1413 0.6211 0.2810
-1.750 0.4159 0.01124 0.00450 -0.1409 0.6116 0.2835
-1.250 0.4696 0.01130 0.00443 -0.1400 0.5938 0.2883
-1.000 0.4958 0.01127 0.00435 -0.1395 0.5846 0.2903
-0.750 0.5226 0.01125 0.00433 -0.1391 0.5753 0.2922
-0.500 0.5485 0.01131 0.00433 -0.1385 0.5651 0.2942
-0.250 0.5753 0.01131 0.00433 -0.1380 0.5559 0.2961
0.000 0.6015 0.01135 0.00430 -0.1374 0.5467 0.2979
0.250 0.6280 0.01136 0.00429 -0.1369 0.5376 0.2996
0.500 0.6537 0.01142 0.00428 -0.1363 0.5271 0.3015
0.750 0.6798 0.01146 0.00429 -0.1357 0.5165 0.3033
1.250 0.7311 0.01150 0.00423 -0.1344 0.4964 0.3063
1.500 0.7559 0.01151 0.00419 -0.1337 0.4872 0.3084
1.750 0.7821 0.01152 0.00422 -0.1332 0.4785 0.3102
2.000 0.8068 0.01162 0.00427 -0.1324 0.4699 0.3122
2.250 0.8328 0.01168 0.00435 -0.1318 0.4620 0.3144
2.500 0.8577 0.01179 0.00442 -0.1311 0.4541 0.3166
2.750 0.8829 0.01189 0.00450 -0.1304 0.4465 0.3186
3.000 0.9079 0.01199 0.00458 -0.1297 0.4384 0.3205
3.250 0.9321 0.01215 0.00468 -0.1288 0.4308 0.3221
3.500 0.9574 0.01225 0.00477 -0.1281 0.4231 0.3235
3.750 0.9808 0.01233 0.00483 -0.1272 0.4153 0.3263
4.000 1.0057 0.01239 0.00493 -0.1264 0.4088 0.3289
4.250 1.0297 0.01250 0.00505 -0.1256 0.4016 0.3314
4.500 1.0526 0.01268 0.00520 -0.1245 0.3946 0.3342
4.750 1.0771 0.01277 0.00532 -0.1237 0.3876 0.3373
5.000 1.1000 0.01293 0.00546 -0.1227 0.3810 0.3399
5.250 1.1226 0.01310 0.00562 -0.1215 0.3752 0.3421
5.500 1.1453 0.01316 0.00573 -0.1204 0.3685 0.3456
5.750 1.1659 0.01331 0.00589 -0.1190 0.3621 0.3493
6.000 1.1875 0.01345 0.00607 -0.1177 0.3564 0.3529
6.250 1.2094 0.01359 0.00623 -0.1164 0.3499 0.3568
6.500 1.2287 0.01383 0.00644 -0.1148 0.3428 0.3605
6.750 1.2506 0.01397 0.00664 -0.1136 0.3364 0.3655
7.000 1.2711 0.01416 0.00688 -0.1122 0.3291 0.3711
7.250 1.2906 0.01441 0.00713 -0.1106 0.3222 0.3778
7.500 1.3113 0.01460 0.00739 -0.1093 0.3143 0.3860
7.750 1.3291 0.01490 0.00769 -0.1075 0.3060 0.3965
8.000 1.3490 0.01512 0.00799 -0.1061 0.2965 0.4115
8.250 1.3661 0.01543 0.00835 -0.1043 0.2862 0.4364
8.500 1.3817 0.01577 0.00878 -0.1023 0.2734 0.4905
8.750 1.4009 0.01549 0.00935 -0.1012 0.2569 1.0000
9.000 1.4144 0.01609 0.00985 -0.0990 0.2386 1.0000
9.250 1.4253 0.01683 0.01047 -0.0965 0.2180 1.0000
9.500 1.4352 0.01764 0.01117 -0.0939 0.2009 1.0000
9.750 1.4455 0.01845 0.01190 -0.0915 0.1890 1.0000
10.250 1.4678 0.02005 0.01343 -0.0871 0.1730 1.0000
10.500 1.4780 0.02093 0.01429 -0.0850 0.1673 1.0000
10.750 1.4901 0.02174 0.01511 -0.0831 0.1626 1.0000
11.000 1.5025 0.02255 0.01594 -0.0813 0.1578 1.0000
11.250 1.5112 0.02360 0.01698 -0.0792 0.1527 1.0000
11.500 1.5226 0.02453 0.01794 -0.0775 0.1475 1.0000
11.750 1.5330 0.02554 0.01897 -0.0758 0.1413 1.0000
12.000 1.5405 0.02679 0.02021 -0.0739 0.1349 1.0000
12.250 1.5496 0.02798 0.02140 -0.0723 0.1257 1.0000
12.500 1.5541 0.02953 0.02291 -0.0705 0.1123 1.0000
12.750 1.5502 0.03179 0.02504 -0.0683 0.0921 1.0000
13.000 1.5460 0.03424 0.02743 -0.0664 0.0825 1.0000
13.250 1.5443 0.03661 0.02981 -0.0648 0.0776 1.0000
13.500 1.5432 0.03907 0.03229 -0.0636 0.0748 1.0000
13.750 1.5418 0.04169 0.03496 -0.0626 0.0726 1.0000
14.000 1.5436 0.04412 0.03747 -0.0618 0.0712 1.0000
14.250 1.5441 0.04677 0.04019 -0.0613 0.0699 1.0000
14.500 1.5437 0.04963 0.04312 -0.0609 0.0690 1.0000
14.750 1.5412 0.05279 0.04636 -0.0606 0.0680 1.0000
15.000 1.5380 0.05611 0.04975 -0.0605 0.0671 1.0000
15.250 1.5330 0.05973 0.05344 -0.0605 0.0663 1.0000
15.500 1.5283 0.06340 0.05718 -0.0607 0.0656 1.0000
15.750 1.5210 0.06748 0.06133 -0.0610 0.0648 1.0000
16.000 1.5196 0.07087 0.06481 -0.0614 0.0645 1.0000
16.250 1.5186 0.07427 0.06830 -0.0618 0.0640 1.0000
16.500 1.5173 0.07778 0.07190 -0.0623 0.0635 1.0000
16.750 1.5162 0.08129 0.07550 -0.0630 0.0628 1.0000
17.000 1.5149 0.08488 0.07917 -0.0637 0.0624 1.0000
17.250 1.5132 0.08859 0.08295 -0.0645 0.0620 1.0000
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