GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 50,000 Max Cl/Cd: 35.24 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe547-il-50000-n5.txt Download as CSV file: xf-goe547-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4147 0.10088 0.09410 -0.0441 1.0000 0.0770
-8.500 -0.4191 0.09829 0.09158 -0.0424 1.0000 0.0766
-8.250 -0.4288 0.09590 0.08928 -0.0406 1.0000 0.0762
-8.000 -0.4453 0.09354 0.08703 -0.0391 1.0000 0.0763
-7.750 -0.4559 0.09073 0.08430 -0.0383 1.0000 0.0761
-7.500 -0.4654 0.08760 0.08124 -0.0380 1.0000 0.0758
-7.250 -0.4735 0.08422 0.07790 -0.0381 1.0000 0.0755
-7.000 -0.4803 0.08043 0.07414 -0.0387 1.0000 0.0751
-6.750 -0.4849 0.07646 0.07016 -0.0395 1.0000 0.0744
-6.500 -0.4876 0.07212 0.06577 -0.0407 1.0000 0.0736
-6.250 -0.4709 0.06550 0.05891 -0.0474 0.9945 0.0727
-6.000 -0.4506 0.05893 0.05194 -0.0540 0.9880 0.0722
-5.750 -0.4276 0.05301 0.04545 -0.0597 0.9818 0.0741
-5.500 -0.4008 0.04794 0.03963 -0.0644 0.9761 0.0758
-5.250 -0.3752 0.04426 0.03535 -0.0666 0.9704 0.0762
-5.000 -0.3455 0.04116 0.03160 -0.0689 0.9654 0.0768
-4.750 -0.3179 0.03869 0.02866 -0.0702 0.9600 0.0777
-4.500 -0.2890 0.03669 0.02634 -0.0714 0.9548 0.0790
-4.250 -0.2576 0.03526 0.02468 -0.0729 0.9503 0.0824
-4.000 -0.2312 0.03404 0.02316 -0.0733 0.9439 0.0864
-3.750 -0.1981 0.03276 0.02144 -0.0746 0.9392 0.0896
-3.500 -0.1690 0.03167 0.02006 -0.0750 0.9339 0.0917
-3.250 -0.1411 0.03070 0.01904 -0.0753 0.9281 0.0950
-3.000 -0.1070 0.02990 0.01810 -0.0767 0.9237 0.0997
-2.750 -0.0806 0.02931 0.01728 -0.0765 0.9173 0.1054
-2.500 -0.0503 0.02870 0.01666 -0.0774 0.9118 0.1164
-2.250 -0.0144 0.02812 0.01614 -0.0793 0.9078 0.1374
-2.000 0.0096 0.02765 0.01585 -0.0791 0.9005 0.1710
-1.750 0.0421 0.02696 0.01566 -0.0806 0.8956 0.2814
-1.500 0.0706 0.02648 0.01580 -0.0811 0.8906 0.4257
-1.250 0.0931 0.02631 0.01588 -0.0801 0.8835 0.5191
-1.000 0.1216 0.02586 0.01586 -0.0797 0.8790 0.6464
-0.750 0.1680 0.02519 0.01576 -0.0828 0.8745 1.0000
-0.500 0.1950 0.02549 0.01573 -0.0831 0.8675 1.0000
-0.250 0.2314 0.02573 0.01566 -0.0850 0.8632 1.0000
0.000 0.2502 0.02615 0.01587 -0.0839 0.8544 1.0000
0.250 0.2837 0.02642 0.01590 -0.0852 0.8495 1.0000
0.500 0.3049 0.02684 0.01617 -0.0845 0.8417 1.0000
0.750 0.3348 0.02716 0.01633 -0.0851 0.8360 1.0000
1.000 0.3610 0.02755 0.01658 -0.0852 0.8295 1.0000
1.250 0.3853 0.02796 0.01688 -0.0849 0.8224 1.0000
1.750 0.4355 0.02880 0.01756 -0.0846 0.8088 1.0000
2.000 0.4697 0.02902 0.01772 -0.0858 0.8042 1.0000
2.250 0.4859 0.02964 0.01830 -0.0843 0.7949 1.0000
2.500 0.5191 0.02985 0.01850 -0.0853 0.7898 1.0000
2.750 0.5363 0.03046 0.01909 -0.0839 0.7804 1.0000
3.000 0.5700 0.03060 0.01925 -0.0848 0.7748 1.0000
3.250 0.5880 0.03115 0.01981 -0.0834 0.7646 1.0000
3.500 0.6272 0.03095 0.01966 -0.0847 0.7589 1.0000
3.750 0.6470 0.03127 0.02003 -0.0833 0.7468 1.0000
4.000 0.6715 0.03139 0.02020 -0.0824 0.7355 1.0000
4.250 0.7152 0.03074 0.01965 -0.0839 0.7287 1.0000
4.500 0.7342 0.03103 0.02003 -0.0823 0.7161 1.0000
4.750 0.7557 0.03126 0.02035 -0.0810 0.7043 1.0000
5.000 0.7837 0.03122 0.02044 -0.0805 0.6942 1.0000
5.250 0.8187 0.03089 0.02027 -0.0808 0.6853 1.0000
5.500 0.8389 0.03116 0.02067 -0.0793 0.6727 1.0000
5.750 0.8625 0.03125 0.02091 -0.0781 0.6603 1.0000
6.000 0.8898 0.03109 0.02095 -0.0773 0.6473 1.0000
6.250 0.9178 0.03082 0.02085 -0.0764 0.6330 1.0000
6.500 0.9444 0.03049 0.02070 -0.0751 0.6161 1.0000
6.750 0.9727 0.03001 0.02038 -0.0739 0.5971 1.0000
7.000 0.9928 0.02985 0.02040 -0.0716 0.5747 1.0000
7.250 1.0134 0.02968 0.02036 -0.0695 0.5500 1.0000
7.500 1.0266 0.02995 0.02075 -0.0666 0.5227 1.0000
7.750 1.0436 0.03017 0.02110 -0.0643 0.4951 1.0000
8.000 1.0622 0.03029 0.02131 -0.0621 0.4633 1.0000
8.250 1.0772 0.03057 0.02151 -0.0593 0.4240 1.0000
8.500 1.0884 0.03121 0.02194 -0.0564 0.3818 1.0000
8.750 1.0951 0.03228 0.02279 -0.0533 0.3424 1.0000
9.000 1.1005 0.03360 0.02397 -0.0504 0.3090 1.0000
9.250 1.1051 0.03509 0.02539 -0.0477 0.2786 1.0000
9.500 1.1070 0.03680 0.02701 -0.0449 0.2474 1.0000
9.750 1.1061 0.03875 0.02889 -0.0423 0.2144 1.0000
10.000 1.1040 0.04089 0.03090 -0.0400 0.1805 1.0000
10.250 1.1006 0.04328 0.03305 -0.0379 0.1493 1.0000
10.500 1.0981 0.04586 0.03541 -0.0361 0.1250 1.0000
10.750 1.0965 0.04857 0.03799 -0.0344 0.1075 1.0000
11.000 1.0963 0.05130 0.04071 -0.0329 0.0917 1.0000
11.250 1.0987 0.05388 0.04334 -0.0315 0.0778 1.0000
11.500 1.1011 0.05650 0.04601 -0.0304 0.0688 1.0000
11.750 1.1061 0.05904 0.04865 -0.0291 0.0624 1.0000
12.000 1.1092 0.06171 0.05133 -0.0281 0.0571 1.0000
12.250 1.1170 0.06417 0.05398 -0.0270 0.0527 1.0000
12.500 1.1264 0.06659 0.05664 -0.0259 0.0487 1.0000
12.750 1.1366 0.06903 0.05921 -0.0249 0.0462 1.0000
13.000 1.1482 0.07158 0.06178 -0.0239 0.0438 1.0000
13.250 1.1526 0.07490 0.06548 -0.0233 0.0423 1.0000
13.500 1.1519 0.07870 0.06963 -0.0230 0.0408 1.0000
13.750 1.1470 0.08286 0.07408 -0.0231 0.0396 1.0000
14.000 1.1396 0.08738 0.07887 -0.0237 0.0387 1.0000
14.250 1.1297 0.09232 0.08407 -0.0247 0.0379 1.0000
14.500 1.1175 0.09781 0.08980 -0.0263 0.0376 1.0000
14.750 1.1022 0.10405 0.09629 -0.0287 0.0374 1.0000
15.000 1.0830 0.11144 0.10392 -0.0322 0.0375 1.0000
15.250 1.0587 0.12058 0.11331 -0.0374 0.0381 1.0000
15.500 1.0286 0.13238 0.12533 -0.0447 0.0391 1.0000
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Polar data table (+)
Polar graphs
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