GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 200,000 Max Cl/Cd: 54.07 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe518-il-200000.txt Download as CSV file: xf-goe518-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-10.000 0.0291 0.10397 0.10042 -0.0975 0.9312 0.0576
-9.750 0.0455 0.09989 0.09632 -0.1024 0.9282 0.0600
-9.500 0.0455 0.09432 0.09075 -0.1112 0.9253 0.0620
-9.250 0.0565 0.09237 0.08883 -0.1083 0.9168 0.0627
-9.000 0.0795 0.08913 0.08558 -0.1108 0.9134 0.0642
-8.750 0.0971 0.08520 0.08164 -0.1156 0.9109 0.0668
-8.500 0.0524 0.08050 0.07697 -0.1233 0.8967 0.0690
-8.250 0.0774 0.07608 0.07255 -0.1255 0.8949 0.0698
-8.000 0.1157 0.07344 0.06990 -0.1262 0.8941 0.0712
-7.750 0.1104 0.07123 0.06771 -0.1250 0.8838 0.0724
-7.500 0.1166 0.06740 0.06384 -0.1284 0.8786 0.0746
-6.750 0.1229 0.05699 0.05321 -0.1311 0.8553 0.0809
-6.500 0.1299 0.05454 0.05068 -0.1303 0.8461 0.0839
-6.250 0.1430 0.04962 0.04542 -0.1337 0.8417 0.0890
-6.000 0.1424 0.04826 0.04408 -0.1291 0.8289 0.0899
-5.750 0.1783 0.04545 0.04115 -0.1325 0.8248 0.0939
-5.500 0.1583 0.04362 0.03886 -0.1257 0.8104 0.0995
-5.250 0.1818 0.04115 0.03646 -0.1258 0.8017 0.1010
-5.000 0.2045 0.03927 0.03452 -0.1256 0.7919 0.1039
-4.750 0.1992 0.03840 0.03312 -0.1199 0.7783 0.1121
-4.500 0.2299 0.03546 0.03025 -0.1215 0.7689 0.1143
-4.250 0.2462 0.03404 0.02876 -0.1196 0.7555 0.1175
-4.000 0.2479 0.03312 0.02745 -0.1146 0.7406 0.1272
-3.750 0.2652 0.03130 0.02564 -0.1131 0.7266 0.1299
-3.500 0.2835 0.03012 0.02432 -0.1113 0.7123 0.1349
-3.250 0.2974 0.02878 0.02265 -0.1087 0.6981 0.1447
-3.000 0.3091 0.02212 0.01421 -0.1008 0.6878 0.0690
-2.750 0.3316 0.02101 0.01290 -0.0994 0.6727 0.0685
-2.500 0.3548 0.02027 0.01189 -0.0981 0.6573 0.0687
-2.250 0.3779 0.01964 0.01101 -0.0968 0.6417 0.0689
-2.000 0.4012 0.01907 0.01021 -0.0955 0.6261 0.0690
-1.750 0.4239 0.01862 0.00955 -0.0942 0.6106 0.0691
-1.500 0.4393 0.01817 0.00902 -0.0915 0.5949 0.0696
-1.250 0.4549 0.01782 0.00861 -0.0888 0.5797 0.0703
-1.000 0.4708 0.01760 0.00832 -0.0863 0.5653 0.0713
-0.750 0.4873 0.01745 0.00809 -0.0839 0.5516 0.0728
-0.500 0.5013 0.01739 0.00794 -0.0810 0.5377 0.0751
-0.250 0.5147 0.01735 0.00782 -0.0780 0.5246 0.0772
0.000 0.5296 0.01726 0.00770 -0.0754 0.5128 0.0801
0.250 0.5450 0.01728 0.00763 -0.0728 0.5014 0.0828
0.500 0.5596 0.01731 0.00761 -0.0701 0.4904 0.0869
1.000 0.5924 0.01735 0.00760 -0.0656 0.4717 0.1079
1.250 0.6013 0.01651 0.00759 -0.0622 0.4648 0.3655
1.500 0.8829 0.01727 0.00928 -0.1148 0.4420 1.0000
1.750 0.8957 0.01747 0.00942 -0.1120 0.4363 1.0000
2.000 0.9129 0.01772 0.00955 -0.1101 0.4310 1.0000
2.250 0.9382 0.01807 0.00972 -0.1098 0.4260 1.0000
2.500 0.9496 0.01827 0.00992 -0.1067 0.4216 1.0000
2.750 0.9645 0.01851 0.01009 -0.1044 0.4169 1.0000
3.000 0.9839 0.01878 0.01026 -0.1030 0.4128 1.0000
3.250 1.0160 0.01921 0.01051 -0.1041 0.4086 1.0000
3.500 1.0270 0.01944 0.01077 -0.1010 0.4053 1.0000
3.750 1.0425 0.01970 0.01102 -0.0989 0.4019 1.0000
4.000 1.0614 0.01999 0.01126 -0.0974 0.3987 1.0000
4.250 1.0828 0.02030 0.01150 -0.0964 0.3956 1.0000
4.500 1.1128 0.02071 0.01179 -0.0972 0.3926 1.0000
4.750 1.1387 0.02115 0.01218 -0.0972 0.3898 1.0000
5.000 1.1507 0.02144 0.01253 -0.0944 0.3873 1.0000
5.250 1.1658 0.02177 0.01287 -0.0922 0.3846 1.0000
5.500 1.1837 0.02210 0.01320 -0.0907 0.3820 1.0000
5.750 1.2039 0.02244 0.01350 -0.0895 0.3793 1.0000
6.000 1.2283 0.02282 0.01382 -0.0893 0.3768 1.0000
6.250 1.2626 0.02335 0.01426 -0.0910 0.3744 1.0000
6.500 1.2867 0.02389 0.01481 -0.0908 0.3723 1.0000
6.750 1.2961 0.02427 0.01527 -0.0877 0.3705 1.0000
7.000 1.3087 0.02470 0.01577 -0.0852 0.3685 1.0000
7.250 1.3237 0.02515 0.01626 -0.0833 0.3665 1.0000
7.500 1.3409 0.02561 0.01675 -0.0818 0.3645 1.0000
7.750 1.3600 0.02607 0.01723 -0.0807 0.3625 1.0000
8.000 1.3819 0.02651 0.01766 -0.0801 0.3606 1.0000
8.250 1.4098 0.02698 0.01808 -0.0806 0.3585 1.0000
8.500 1.4473 0.02771 0.01876 -0.0831 0.3564 1.0000
8.750 1.4614 0.02837 0.01950 -0.0813 0.3549 1.0000
9.000 1.4666 0.02895 0.02020 -0.0777 0.3535 1.0000
9.250 1.4736 0.02960 0.02095 -0.0746 0.3519 1.0000
9.500 1.4815 0.03029 0.02175 -0.0718 0.3503 1.0000
9.750 1.4902 0.03098 0.02254 -0.0692 0.3485 1.0000
10.000 1.4996 0.03159 0.02321 -0.0667 0.3463 1.0000
10.250 1.5140 0.03215 0.02380 -0.0651 0.3443 1.0000
10.500 1.5374 0.03253 0.02417 -0.0650 0.3420 1.0000
10.750 1.5720 0.03302 0.02460 -0.0668 0.3398 1.0000
11.000 1.5872 0.03397 0.02560 -0.0656 0.3378 1.0000
11.250 1.5751 0.03493 0.02675 -0.0599 0.3359 1.0000
11.500 1.5682 0.03598 0.02796 -0.0554 0.3338 1.0000
11.750 1.5655 0.03699 0.02908 -0.0518 0.3313 1.0000
12.000 1.5684 0.03796 0.03015 -0.0490 0.3292 1.0000
12.250 1.5788 0.03866 0.03089 -0.0473 0.3269 1.0000
12.500 1.6035 0.03891 0.03112 -0.0475 0.3246 1.0000
12.750 1.6465 0.03901 0.03113 -0.0502 0.3223 1.0000
13.000 1.6366 0.04059 0.03287 -0.0460 0.3204 1.0000
13.250 1.6054 0.04293 0.03546 -0.0397 0.3184 1.0000
13.500 1.5780 0.04558 0.03831 -0.0346 0.3161 1.0000
13.750 1.5575 0.04813 0.04102 -0.0307 0.3135 1.0000
14.000 1.5521 0.05000 0.04300 -0.0284 0.3111 1.0000
14.250 1.5697 0.05049 0.04351 -0.0280 0.3089 1.0000
14.500 1.6068 0.04994 0.04291 -0.0291 0.3070 1.0000
14.750 1.6638 0.04891 0.04179 -0.0323 0.3049 1.0000
15.000 0.9865 0.12904 0.12303 -0.0245 0.2577 1.0000
16.000 1.4615 0.07394 0.06770 -0.0160 0.2888 1.0000
16.250 0.9536 0.14993 0.14413 -0.0303 0.2213 1.0000
16.500 0.9722 0.14995 0.14417 -0.0302 0.2193 1.0000
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Polar data table (+)
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