GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 424 AIRFOIL (goe424-il) Reynolds number: 200,000 Max Cl/Cd: 63.34 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe424-il-200000-n5.txt Download as CSV file: xf-goe424-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 424 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4521 0.07178 0.06767 -0.0970 0.9852 0.0299
-13.250 -0.5003 0.06054 0.05604 -0.1068 0.9781 0.0300
-13.000 -0.5159 0.05486 0.05012 -0.1118 0.9708 0.0302
-12.750 -0.5147 0.05198 0.04714 -0.1139 0.9618 0.0305
-12.500 -0.5088 0.04954 0.04459 -0.1159 0.9535 0.0308
-12.250 -0.5074 0.04721 0.04213 -0.1166 0.9421 0.0311
-12.000 -0.5101 0.04499 0.03975 -0.1160 0.9283 0.0315
-11.750 -0.5142 0.04287 0.03742 -0.1144 0.9129 0.0319
-11.500 -0.5191 0.04086 0.03517 -0.1120 0.8959 0.0325
-11.250 -0.5227 0.03881 0.03281 -0.1092 0.8785 0.0332
-11.000 -0.5307 0.03606 0.02947 -0.1058 0.8605 0.0344
-10.750 -0.5125 0.03503 0.02835 -0.1051 0.8429 0.0349
-10.500 -0.4948 0.03411 0.02730 -0.1042 0.8239 0.0354
-10.250 -0.4783 0.03310 0.02611 -0.1031 0.8034 0.0361
-10.000 -0.4628 0.03197 0.02473 -0.1018 0.7819 0.0368
-9.750 -0.4477 0.03084 0.02327 -0.1003 0.7597 0.0378
-9.500 -0.4341 0.02966 0.02164 -0.0984 0.7374 0.0390
-9.250 -0.4152 0.02870 0.02046 -0.0973 0.7157 0.0397
-9.000 -0.3944 0.02795 0.01956 -0.0965 0.6958 0.0403
-8.750 -0.3735 0.02723 0.01867 -0.0956 0.6790 0.0410
-8.250 -0.3315 0.02587 0.01691 -0.0938 0.6529 0.0431
-8.000 -0.3101 0.02521 0.01598 -0.0929 0.6431 0.0441
-7.750 -0.2875 0.02453 0.01510 -0.0921 0.6341 0.0448
-7.500 -0.2633 0.02378 0.01430 -0.0918 0.6263 0.0455
-7.250 -0.2395 0.02320 0.01366 -0.0914 0.6188 0.0464
-7.000 -0.2159 0.02270 0.01306 -0.0908 0.6123 0.0475
-6.750 -0.1918 0.02218 0.01247 -0.0903 0.6065 0.0486
-6.500 -0.1676 0.02169 0.01187 -0.0898 0.6010 0.0495
-6.250 -0.1434 0.02127 0.01133 -0.0892 0.5962 0.0502
-6.000 -0.1195 0.02078 0.01077 -0.0887 0.5921 0.0511
-5.750 -0.0963 0.02020 0.01025 -0.0882 0.5878 0.0521
-5.500 -0.0731 0.01977 0.00981 -0.0875 0.5837 0.0533
-5.250 -0.0500 0.01940 0.00939 -0.0869 0.5799 0.0545
-5.000 -0.0270 0.01907 0.00899 -0.0861 0.5764 0.0555
-4.750 -0.0037 0.01876 0.00862 -0.0855 0.5730 0.0564
-4.500 0.0199 0.01848 0.00831 -0.0848 0.5692 0.0574
-4.250 0.0413 0.01804 0.00789 -0.0839 0.5657 0.0588
-4.000 0.0642 0.01774 0.00756 -0.0832 0.5625 0.0605
-3.750 0.0881 0.01752 0.00727 -0.0827 0.5597 0.0622
-3.500 0.1128 0.01735 0.00701 -0.0822 0.5571 0.0637
-3.250 0.1379 0.01720 0.00679 -0.0818 0.5546 0.0653
-3.000 0.1622 0.01698 0.00656 -0.0814 0.5518 0.0677
-2.750 0.1871 0.01682 0.00638 -0.0810 0.5488 0.0711
-2.500 0.2122 0.01667 0.00623 -0.0806 0.5459 0.0757
-2.250 0.2369 0.01649 0.00608 -0.0801 0.5432 0.0859
-2.000 0.2562 0.01575 0.00584 -0.0791 0.5409 0.2255
-1.750 0.2746 0.01503 0.00575 -0.0779 0.5389 0.3895
-1.500 0.2986 0.01486 0.00577 -0.0774 0.5368 0.4503
-1.250 0.3223 0.01472 0.00583 -0.0767 0.5345 0.5022
-1.000 0.3471 0.01466 0.00590 -0.0762 0.5319 0.5405
-0.750 0.3720 0.01463 0.00597 -0.0757 0.5292 0.5782
-0.500 0.3972 0.01461 0.00604 -0.0753 0.5267 0.6109
-0.250 0.4228 0.01461 0.00611 -0.0748 0.5246 0.6420
0.000 0.4489 0.01464 0.00619 -0.0746 0.5226 0.6702
0.250 0.4755 0.01470 0.00628 -0.0743 0.5208 0.6978
0.500 0.5014 0.01476 0.00641 -0.0740 0.5187 0.7262
0.750 0.5260 0.01480 0.00658 -0.0733 0.5162 0.7558
1.000 0.5509 0.01488 0.00676 -0.0726 0.5138 0.7875
1.250 0.5765 0.01498 0.00695 -0.0721 0.5115 0.8167
1.500 0.6027 0.01510 0.00711 -0.0717 0.5093 0.8429
1.750 0.6303 0.01523 0.00726 -0.0717 0.5070 0.8635
2.000 0.6589 0.01538 0.00738 -0.0719 0.5049 0.8808
2.250 0.6902 0.01556 0.00752 -0.0727 0.5030 0.8953
2.500 0.7216 0.01577 0.00771 -0.0735 0.5009 0.9093
2.750 0.7514 0.01595 0.00795 -0.0742 0.4983 0.9233
3.000 0.7818 0.01614 0.00816 -0.0750 0.4956 0.9367
3.250 0.8162 0.01634 0.00836 -0.0767 0.4930 0.9470
3.500 0.8500 0.01653 0.00853 -0.0782 0.4904 0.9569
3.750 0.8834 0.01670 0.00868 -0.0797 0.4880 0.9672
4.000 0.9223 0.01690 0.00882 -0.0824 0.4857 0.9743
4.250 0.9608 0.01713 0.00906 -0.0850 0.4830 0.9829
4.500 0.9999 0.01737 0.00936 -0.0880 0.4796 0.9912
4.750 1.0389 0.01753 0.00955 -0.0909 0.4754 0.9978
5.000 1.0620 0.01761 0.00961 -0.0904 0.4715 1.0000
5.250 1.0795 0.01768 0.00961 -0.0887 0.4682 1.0000
5.500 1.0920 0.01783 0.00980 -0.0862 0.4647 1.0000
5.750 1.1045 0.01800 0.01003 -0.0836 0.4612 1.0000
6.000 1.1194 0.01817 0.01022 -0.0815 0.4580 1.0000
6.250 1.1360 0.01833 0.01039 -0.0797 0.4552 1.0000
6.500 1.1550 0.01847 0.01051 -0.0783 0.4525 1.0000
6.750 1.1742 0.01865 0.01068 -0.0771 0.4496 1.0000
7.000 1.1864 0.01891 0.01104 -0.0746 0.4457 1.0000
7.250 1.2011 0.01914 0.01132 -0.0725 0.4419 1.0000
7.500 1.2168 0.01934 0.01154 -0.0707 0.4385 1.0000
7.750 1.2357 0.01951 0.01171 -0.0694 0.4355 1.0000
8.000 1.2509 0.01980 0.01205 -0.0676 0.4321 1.0000
8.250 1.2625 0.02017 0.01251 -0.0652 0.4277 1.0000
8.500 1.2768 0.02049 0.01288 -0.0634 0.4234 1.0000
8.750 1.2943 0.02073 0.01313 -0.0621 0.4195 1.0000
9.000 1.3072 0.02117 0.01364 -0.0602 0.4148 1.0000
9.250 1.3189 0.02167 0.01423 -0.0582 0.4094 1.0000
9.500 1.3340 0.02206 0.01465 -0.0567 0.4048 1.0000
9.750 1.3469 0.02259 0.01523 -0.0551 0.3997 1.0000
10.000 1.3566 0.02327 0.01600 -0.0531 0.3933 1.0000
10.250 1.3694 0.02381 0.01653 -0.0516 0.3875 1.0000
10.500 1.3768 0.02471 0.01753 -0.0496 0.3802 1.0000
10.750 1.3858 0.02552 0.01836 -0.0479 0.3728 1.0000
11.000 1.3917 0.02662 0.01953 -0.0460 0.3646 1.0000
11.250 1.3988 0.02769 0.02058 -0.0443 0.3568 1.0000
11.500 1.4027 0.02909 0.02206 -0.0426 0.3481 1.0000
11.750 1.4062 0.03054 0.02350 -0.0410 0.3395 1.0000
12.000 1.4072 0.03232 0.02532 -0.0394 0.3300 1.0000
12.250 1.4082 0.03417 0.02718 -0.0379 0.3213 1.0000
12.500 1.4082 0.03619 0.02922 -0.0366 0.3128 1.0000
12.750 1.4088 0.03831 0.03138 -0.0354 0.3050 1.0000
13.000 1.4082 0.04057 0.03365 -0.0344 0.2972 1.0000
13.250 1.4082 0.04289 0.03602 -0.0335 0.2901 1.0000
13.500 1.4079 0.04529 0.03845 -0.0327 0.2830 1.0000
13.750 1.4084 0.04764 0.04082 -0.0320 0.2766 1.0000
14.000 1.4077 0.05020 0.04344 -0.0314 0.2697 1.0000
14.250 1.4080 0.05259 0.04579 -0.0307 0.2634 1.0000
14.500 1.4066 0.05536 0.04866 -0.0303 0.2566 1.0000
14.750 1.4059 0.05796 0.05126 -0.0299 0.2499 1.0000
15.000 1.4054 0.06063 0.05398 -0.0296 0.2437 1.0000
15.250 1.4041 0.06342 0.05682 -0.0293 0.2372 1.0000
15.500 1.4050 0.06591 0.05929 -0.0290 0.2315 1.0000
15.750 1.4039 0.06882 0.06230 -0.0289 0.2257 1.0000
16.000 1.4039 0.07152 0.06503 -0.0288 0.2199 1.0000
16.250 1.4046 0.07415 0.06768 -0.0287 0.2148 1.0000
16.500 1.4043 0.07703 0.07066 -0.0288 0.2093 1.0000
16.750 1.4037 0.07989 0.07354 -0.0289 0.2040 1.0000
17.000 1.4049 0.08256 0.07626 -0.0290 0.1992 1.0000
17.250 1.4040 0.08560 0.07941 -0.0292 0.1941 1.0000
17.500 1.4029 0.08858 0.08242 -0.0294 0.1886 1.0000
17.750 1.4011 0.09174 0.08565 -0.0298 0.1833 1.0000
18.000 1.3980 0.09513 0.08911 -0.0302 0.1772 1.0000
18.250 1.3947 0.09850 0.09249 -0.0307 0.1713 1.0000
18.500 1.3907 0.10209 0.09619 -0.0314 0.1649 1.0000
18.750 1.3851 0.10582 0.09993 -0.0321 0.1585 1.0000
19.000 1.3812 0.10945 0.10366 -0.0328 0.1516 1.0000
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Polar data table (+)
Polar graphs
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