GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 50,000 Max Cl/Cd: 40.06 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe450-il-50000-n5.txt Download as CSV file: xf-goe450-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3462 0.10697 0.10052 -0.0290 1.0000 0.1072
-7.500 -0.3636 0.10656 0.10025 -0.0279 1.0000 0.1084
-7.250 -0.3772 0.10582 0.09963 -0.0292 1.0000 0.1092
-7.000 -0.3844 0.10416 0.09808 -0.0311 1.0000 0.1097
-6.750 -0.3765 0.09924 0.09319 -0.0254 1.0000 0.1117
-6.500 -0.3759 0.09658 0.09057 -0.0234 1.0000 0.1140
-6.250 -0.3774 0.09434 0.08838 -0.0226 1.0000 0.1173
-5.750 -0.3433 0.08689 0.08088 -0.0323 0.9895 0.1295
-5.250 -0.2913 0.07876 0.07262 -0.0445 0.9757 0.1441
-4.750 -0.2358 0.07116 0.06484 -0.0552 0.9621 0.1610
-4.500 -0.2114 0.06791 0.06152 -0.0591 0.9539 0.1756
-4.000 -0.1003 0.05263 0.04492 -0.0840 0.9413 0.0784
-3.750 -0.0631 0.04902 0.04104 -0.0885 0.9360 0.0767
-3.500 -0.0259 0.04576 0.03734 -0.0928 0.9297 0.0776
-3.250 0.0105 0.04287 0.03403 -0.0962 0.9233 0.0774
-3.000 0.0526 0.04005 0.03074 -0.1003 0.9191 0.0762
-2.750 0.0840 0.03798 0.02824 -0.1019 0.9112 0.0756
-2.500 0.1233 0.03596 0.02575 -0.1047 0.9060 0.0754
-2.250 0.1596 0.03443 0.02377 -0.1067 0.8999 0.0770
-2.000 0.1937 0.03327 0.02212 -0.1080 0.8927 0.0795
-1.750 0.2343 0.03195 0.02049 -0.1104 0.8883 0.0809
-1.500 0.2611 0.03114 0.01951 -0.1105 0.8792 0.0821
-1.250 0.2995 0.03020 0.01838 -0.1123 0.8742 0.0842
-1.000 0.3270 0.02970 0.01771 -0.1121 0.8651 0.0866
-0.750 0.3657 0.02904 0.01683 -0.1138 0.8598 0.0911
-0.500 0.3930 0.02871 0.01641 -0.1137 0.8504 0.0979
-0.250 0.4310 0.02813 0.01573 -0.1153 0.8448 0.1088
0.000 0.4576 0.02783 0.01545 -0.1152 0.8349 0.1209
0.250 0.4963 0.02694 0.01491 -0.1170 0.8295 0.1805
0.500 0.5152 0.02497 0.01490 -0.1151 0.8193 1.0000
0.750 0.5488 0.02500 0.01457 -0.1157 0.8121 1.0000
1.000 0.5756 0.02520 0.01454 -0.1154 0.8021 1.0000
1.250 0.6024 0.02541 0.01457 -0.1151 0.7922 1.0000
1.500 0.6359 0.02536 0.01437 -0.1156 0.7850 1.0000
1.750 0.6597 0.02566 0.01456 -0.1149 0.7739 1.0000
2.000 0.6907 0.02569 0.01448 -0.1151 0.7658 1.0000
2.250 0.7182 0.02583 0.01456 -0.1148 0.7561 1.0000
2.500 0.7433 0.02609 0.01477 -0.1142 0.7455 1.0000
2.750 0.7772 0.02596 0.01459 -0.1147 0.7385 1.0000
3.000 0.7998 0.02633 0.01497 -0.1138 0.7268 1.0000
3.250 0.8262 0.02655 0.01518 -0.1133 0.7168 1.0000
3.500 0.8578 0.02651 0.01514 -0.1135 0.7087 1.0000
3.750 0.8807 0.02691 0.01559 -0.1126 0.6970 1.0000
4.000 0.9075 0.02713 0.01585 -0.1122 0.6871 1.0000
4.250 0.9379 0.02716 0.01593 -0.1122 0.6782 1.0000
4.500 0.9604 0.02761 0.01648 -0.1112 0.6664 1.0000
4.750 0.9862 0.02792 0.01687 -0.1107 0.6559 1.0000
5.000 1.0172 0.02795 0.01698 -0.1107 0.6470 1.0000
5.250 1.0385 0.02851 0.01765 -0.1097 0.6347 1.0000
5.500 1.0621 0.02897 0.01826 -0.1089 0.6235 1.0000
5.750 1.0911 0.02912 0.01852 -0.1086 0.6134 1.0000
6.000 1.1163 0.02941 0.01894 -0.1079 0.6012 1.0000
6.250 1.1377 0.02985 0.01956 -0.1066 0.5874 1.0000
6.500 1.1599 0.03017 0.02003 -0.1053 0.5729 1.0000
6.750 1.1820 0.03043 0.02042 -0.1039 0.5575 1.0000
7.000 1.2032 0.03076 0.02092 -0.1025 0.5423 1.0000
7.250 1.2238 0.03114 0.02150 -0.1010 0.5272 1.0000
7.500 1.2458 0.03110 0.02156 -0.0992 0.5081 1.0000
7.750 1.2562 0.03148 0.02206 -0.0960 0.4832 1.0000
8.000 1.2676 0.03171 0.02231 -0.0928 0.4551 1.0000
8.250 1.2770 0.03215 0.02280 -0.0895 0.4256 1.0000
8.500 1.2831 0.03284 0.02348 -0.0860 0.3954 1.0000
8.750 1.2862 0.03381 0.02444 -0.0823 0.3636 1.0000
9.000 1.2886 0.03504 0.02567 -0.0790 0.3307 1.0000
9.250 1.2887 0.03659 0.02718 -0.0757 0.2926 1.0000
9.500 1.2850 0.03859 0.02905 -0.0726 0.2425 1.0000
9.750 1.2754 0.04132 0.03138 -0.0694 0.1935 1.0000
10.000 1.2645 0.04458 0.03431 -0.0667 0.1598 1.0000
10.250 1.2562 0.04792 0.03752 -0.0646 0.1331 1.0000
10.500 1.2496 0.05126 0.04083 -0.0628 0.1139 1.0000
10.750 1.2439 0.05462 0.04414 -0.0613 0.1019 1.0000
11.000 1.2392 0.05796 0.04744 -0.0601 0.0934 1.0000
11.250 1.2345 0.06135 0.05081 -0.0590 0.0869 1.0000
11.500 1.2340 0.06434 0.05388 -0.0578 0.0811 1.0000
11.750 1.2351 0.06716 0.05679 -0.0566 0.0763 1.0000
12.000 1.2361 0.06995 0.05953 -0.0553 0.0719 1.0000
12.250 1.2427 0.07231 0.06218 -0.0541 0.0669 1.0000
12.500 1.2496 0.07459 0.06458 -0.0528 0.0630 1.0000
12.750 1.2606 0.07649 0.06653 -0.0512 0.0596 1.0000
13.000 1.2693 0.07894 0.06933 -0.0501 0.0560 1.0000
13.250 1.2762 0.08151 0.07209 -0.0492 0.0530 1.0000
13.500 1.2889 0.08355 0.07418 -0.0478 0.0507 1.0000
13.750 1.2943 0.08682 0.07772 -0.0470 0.0489 1.0000
14.000 1.2908 0.09104 0.08231 -0.0471 0.0475 1.0000
14.250 1.2845 0.09561 0.08718 -0.0476 0.0462 1.0000
14.500 1.2762 0.10050 0.09235 -0.0485 0.0452 1.0000
14.750 1.2660 0.10585 0.09796 -0.0500 0.0445 1.0000
15.000 1.2534 0.11180 0.10417 -0.0521 0.0440 1.0000
15.250 1.2377 0.11863 0.11125 -0.0552 0.0438 1.0000
15.500 1.2183 0.12664 0.11950 -0.0595 0.0439 1.0000
15.750 1.1928 0.13684 0.12995 -0.0658 0.0445 1.0000
16.000 1.1625 0.14980 0.14311 -0.0745 0.0455 1.0000
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Polar data table (+)
Polar graphs
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