GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 447 AIRFOIL (goe447-il) Reynolds number: 200,000 Max Cl/Cd: 84.02 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe447-il-200000.txt Download as CSV file: xf-goe447-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 447 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0581 0.10522 0.10124 -0.1160 0.9128 0.0496
-10.000 0.0633 0.10317 0.09918 -0.1179 0.9046 0.0511
-9.750 0.0525 0.10318 0.09914 -0.1232 0.8959 0.0518
-9.500 0.0712 0.09841 0.09437 -0.1215 0.8907 0.0522
-9.250 0.0854 0.09532 0.09125 -0.1209 0.8852 0.0528
-9.000 0.0962 0.09287 0.08875 -0.1212 0.8803 0.0537
-8.750 0.1054 0.09067 0.08655 -0.1220 0.8741 0.0547
-8.500 0.1140 0.08844 0.08430 -0.1230 0.8682 0.0559
-8.250 0.1220 0.08622 0.08203 -0.1245 0.8633 0.0574
-8.000 0.1177 0.08540 0.08124 -0.1296 0.8544 0.0589
-7.750 0.1183 0.08353 0.07935 -0.1364 0.8479 0.0592
-7.500 0.1324 0.07979 0.07559 -0.1321 0.8450 0.0597
-7.250 0.1475 0.07715 0.07295 -0.1304 0.8403 0.0604
-7.000 0.1588 0.07509 0.07088 -0.1304 0.8355 0.0615
-6.750 0.1712 0.07292 0.06868 -0.1319 0.8316 0.0629
-6.500 0.1833 0.07075 0.06649 -0.1344 0.8271 0.0645
-6.250 0.2060 0.06838 0.06402 -0.1501 0.8196 0.0676
-6.000 0.2215 0.06465 0.06025 -0.1527 0.8158 0.0681
-5.750 0.2345 0.06209 0.05767 -0.1507 0.8131 0.0686
-5.500 0.2465 0.06023 0.05584 -0.1497 0.8087 0.0694
-5.250 0.2616 0.05834 0.05396 -0.1501 0.8041 0.0704
-5.000 0.2813 0.05617 0.05175 -0.1521 0.8004 0.0721
-4.750 0.3312 0.05162 0.04679 -0.1677 0.7968 0.0781
-4.500 0.3424 0.04940 0.04464 -0.1659 0.7926 0.0787
-4.250 0.3566 0.04774 0.04301 -0.1649 0.7874 0.0796
-4.000 0.3778 0.04588 0.04110 -0.1654 0.7834 0.0809
-3.750 0.4053 0.04371 0.03882 -0.1675 0.7801 0.0834
-3.500 0.4459 0.03966 0.03430 -0.1749 0.7754 0.0902
-3.250 0.4628 0.03806 0.03276 -0.1740 0.7700 0.0913
-3.000 0.4870 0.03653 0.03120 -0.1743 0.7661 0.0931
-2.750 0.5253 0.03390 0.02807 -0.1782 0.7631 0.1039
-2.500 0.5448 0.03264 0.02691 -0.1776 0.7588 0.1059
-2.250 0.5791 0.02661 0.02001 -0.1797 0.7544 0.0751
-2.000 0.6082 0.02444 0.01742 -0.1803 0.7508 0.0727
-1.750 0.6392 0.02302 0.01565 -0.1809 0.7480 0.0738
-1.500 0.6716 0.02225 0.01444 -0.1815 0.7456 0.0774
-1.250 0.6936 0.02144 0.01355 -0.1808 0.7409 0.0800
-1.000 0.7185 0.02103 0.01312 -0.1804 0.7363 0.0839
-0.750 0.7484 0.02037 0.01222 -0.1806 0.7329 0.0907
-0.500 0.7795 0.01986 0.01166 -0.1812 0.7301 0.1006
-0.250 0.8061 0.01939 0.01119 -0.1810 0.7263 0.1099
0.000 0.8281 0.01942 0.01119 -0.1801 0.7210 0.1183
0.250 0.8560 0.01905 0.01087 -0.1802 0.7172 0.1282
0.500 0.8868 0.01869 0.01048 -0.1807 0.7142 0.1378
0.750 0.9168 0.01846 0.01025 -0.1811 0.7110 0.1447
1.000 0.9362 0.01861 0.01045 -0.1796 0.7047 0.1494
1.250 0.9646 0.01831 0.01021 -0.1797 0.7005 0.1552
1.500 0.9965 0.01802 0.00989 -0.1803 0.6972 0.1632
1.750 1.0208 0.01803 0.00999 -0.1798 0.6921 0.1749
2.000 1.0446 0.01800 0.01010 -0.1791 0.6865 0.2009
2.250 1.0737 0.01749 0.01006 -0.1794 0.6825 0.3765
2.500 1.1054 0.01632 0.00980 -0.1797 0.6794 1.0000
2.750 1.1226 0.01666 0.01015 -0.1778 0.6722 1.0000
3.000 1.1511 0.01661 0.01000 -0.1778 0.6670 1.0000
3.250 1.1851 0.01645 0.00967 -0.1788 0.6627 1.0000
3.500 1.2019 0.01667 0.00994 -0.1768 0.6541 1.0000
3.750 1.2334 0.01650 0.00964 -0.1773 0.6485 1.0000
4.000 1.2546 0.01667 0.00981 -0.1761 0.6410 1.0000
4.250 1.2811 0.01667 0.00976 -0.1758 0.6344 1.0000
4.500 1.3091 0.01670 0.00973 -0.1758 0.6286 1.0000
4.750 1.3290 0.01687 0.00991 -0.1744 0.6201 1.0000
5.000 1.3605 0.01678 0.00971 -0.1750 0.6141 1.0000
5.250 1.3762 0.01704 0.01004 -0.1729 0.6045 1.0000
5.500 1.4068 0.01701 0.00990 -0.1733 0.5982 1.0000
5.750 1.4216 0.01730 0.01027 -0.1710 0.5885 1.0000
6.000 1.4506 0.01733 0.01020 -0.1713 0.5818 1.0000
6.250 1.4647 0.01766 0.01062 -0.1689 0.5722 1.0000
6.500 1.4914 0.01775 0.01064 -0.1688 0.5652 1.0000
6.750 1.5054 0.01810 0.01106 -0.1664 0.5559 1.0000
7.000 1.5297 0.01826 0.01117 -0.1658 0.5486 1.0000
7.250 1.5428 0.01862 0.01159 -0.1633 0.5392 1.0000
7.500 1.5646 0.01886 0.01179 -0.1624 0.5319 1.0000
7.750 1.5771 0.01926 0.01227 -0.1598 0.5240 1.0000
8.000 1.6017 0.01951 0.01245 -0.1594 0.5177 1.0000
8.250 1.6108 0.02004 0.01308 -0.1563 0.5100 1.0000
8.500 1.6330 0.02034 0.01335 -0.1555 0.5035 1.0000
8.750 1.6443 0.02090 0.01400 -0.1530 0.4962 1.0000
9.000 1.6616 0.02130 0.01439 -0.1514 0.4887 1.0000
9.250 1.6713 0.02191 0.01506 -0.1487 0.4800 1.0000
9.750 1.6902 0.02320 0.01637 -0.1433 0.4603 1.0000
10.000 1.6994 0.02393 0.01710 -0.1407 0.4499 1.0000
10.250 1.7096 0.02468 0.01782 -0.1383 0.4396 1.0000
10.500 1.7123 0.02577 0.01901 -0.1351 0.4295 1.0000
10.750 1.7201 0.02671 0.01993 -0.1326 0.4190 1.0000
11.000 1.7235 0.02790 0.02115 -0.1297 0.4082 1.0000
11.250 1.7257 0.02924 0.02260 -0.1269 0.3975 1.0000
11.500 1.7294 0.03056 0.02392 -0.1243 0.3866 1.0000
11.750 1.7295 0.03215 0.02556 -0.1215 0.3745 1.0000
12.000 1.7278 0.03399 0.02749 -0.1188 0.3615 1.0000
12.250 1.7262 0.03591 0.02948 -0.1162 0.3479 1.0000
12.500 1.7236 0.03804 0.03164 -0.1138 0.3328 1.0000
12.750 1.7192 0.04042 0.03405 -0.1113 0.3156 1.0000
13.000 1.7117 0.04317 0.03676 -0.1088 0.2966 1.0000
13.250 1.7026 0.04621 0.03973 -0.1064 0.2773 1.0000
13.500 1.6935 0.04938 0.04283 -0.1042 0.2595 1.0000
13.750 1.6856 0.05253 0.04593 -0.1022 0.2447 1.0000
14.000 1.6781 0.05574 0.04910 -0.1003 0.2315 1.0000
14.250 1.6697 0.05915 0.05247 -0.0986 0.2183 1.0000
14.500 1.6615 0.06265 0.05594 -0.0971 0.2056 1.0000
14.750 1.6529 0.06629 0.05959 -0.0957 0.1918 1.0000
15.000 1.6422 0.07028 0.06356 -0.0944 0.1769 1.0000
15.250 1.6293 0.07469 0.06795 -0.0934 0.1584 1.0000
15.500 1.6123 0.07975 0.07292 -0.0924 0.1245 1.0000
15.750 1.5825 0.08643 0.07928 -0.0916 0.0854 1.0000
16.000 1.5590 0.09247 0.08519 -0.0909 0.0683 1.0000
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