GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 287 AIRFOIL (goe287-il) Reynolds number: 100,000 Max Cl/Cd: 58.26 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe287-il-100000.txt Download as CSV file: xf-goe287-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 287 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3359 0.09949 0.09521 -0.0161 1.0000 0.0625
-7.750 -0.3331 0.09730 0.09311 -0.0205 1.0000 0.0646
-7.500 -0.3274 0.09584 0.09173 -0.0313 1.0000 0.0657
-7.250 -0.3164 0.09402 0.08990 -0.0414 1.0000 0.0662
-7.000 -0.3111 0.08660 0.08262 -0.0298 1.0000 0.0687
-6.750 -0.3121 0.08447 0.08060 -0.0283 1.0000 0.0707
-6.500 -0.3146 0.08281 0.07902 -0.0288 0.9951 0.0725
-6.250 -0.2518 0.07827 0.07414 -0.0544 0.9783 0.0802
-6.000 -0.2273 0.07126 0.06722 -0.0562 0.9711 0.0823
-5.750 -0.1986 0.06698 0.06292 -0.0587 0.9590 0.0869
-5.500 -0.1537 0.06260 0.05820 -0.0723 0.9412 0.0961
-5.250 -0.1383 0.05906 0.05474 -0.0704 0.9253 0.1005
-5.000 -0.1047 0.05599 0.05128 -0.0779 0.9070 0.1106
-4.750 -0.0916 0.05276 0.04812 -0.0759 0.8920 0.1142
-4.500 -0.0640 0.05009 0.04512 -0.0795 0.8777 0.1258
-4.250 -0.0481 0.04746 0.04251 -0.0782 0.8653 0.1321
-4.000 -0.0260 0.04500 0.03986 -0.0791 0.8546 0.1455
-3.750 -0.0035 0.04279 0.03750 -0.0798 0.8438 0.1616
-3.500 0.0229 0.04090 0.03533 -0.0816 0.8335 0.1859
-3.250 0.0428 0.03869 0.03309 -0.0809 0.8255 0.2038
-3.000 0.0654 0.03691 0.03122 -0.0811 0.8160 0.2339
-2.250 0.1203 0.03192 0.02635 -0.0769 0.7945 0.3841
-2.000 0.1405 0.03026 0.02474 -0.0755 0.7877 0.4350
-1.750 0.2374 0.02716 0.01912 -0.0871 0.7831 0.1418
-1.500 0.2709 0.02571 0.01725 -0.0874 0.7764 0.1164
-1.250 0.3021 0.02539 0.01638 -0.0870 0.7708 0.1096
-1.000 0.3305 0.02428 0.01511 -0.0870 0.7660 0.1084
-0.750 0.3598 0.02345 0.01419 -0.0874 0.7598 0.1060
-0.500 0.3874 0.02276 0.01335 -0.0868 0.7544 0.1046
-0.250 0.4153 0.02228 0.01280 -0.0867 0.7467 0.1046
0.000 0.4415 0.02172 0.01214 -0.0856 0.7395 0.1060
0.250 0.4683 0.02142 0.01180 -0.0852 0.7308 0.1094
0.500 0.4931 0.02075 0.01119 -0.0840 0.7239 0.1185
0.750 0.5197 0.02052 0.01097 -0.0837 0.7152 0.1275
1.000 0.5465 0.02009 0.01049 -0.0827 0.7089 0.1478
1.250 0.5725 0.01802 0.01031 -0.0819 0.7005 1.0000
1.500 0.5990 0.01807 0.01005 -0.0809 0.6943 1.0000
1.750 0.6261 0.01843 0.01031 -0.0811 0.6864 1.0000
2.000 0.6528 0.01854 0.01027 -0.0805 0.6804 1.0000
2.250 0.6795 0.01886 0.01054 -0.0804 0.6727 1.0000
2.500 0.7062 0.01896 0.01053 -0.0798 0.6660 1.0000
2.750 0.7327 0.01925 0.01080 -0.0797 0.6579 1.0000
3.000 0.7594 0.01932 0.01081 -0.0790 0.6510 1.0000
3.250 0.7857 0.01962 0.01111 -0.0789 0.6422 1.0000
3.500 0.8126 0.01960 0.01101 -0.0781 0.6352 1.0000
3.750 0.8386 0.01987 0.01135 -0.0778 0.6247 1.0000
4.000 0.8650 0.01996 0.01142 -0.0772 0.6153 1.0000
4.250 0.8917 0.01990 0.01130 -0.0764 0.6057 1.0000
4.500 0.9176 0.02000 0.01145 -0.0758 0.5929 1.0000
4.750 0.9435 0.02004 0.01154 -0.0751 0.5796 1.0000
5.000 0.9696 0.02004 0.01155 -0.0743 0.5653 1.0000
5.250 0.9956 0.02004 0.01155 -0.0735 0.5497 1.0000
5.500 1.0217 0.02002 0.01154 -0.0727 0.5328 1.0000
5.750 1.0474 0.02008 0.01159 -0.0719 0.5142 1.0000
6.000 1.0724 0.02029 0.01187 -0.0713 0.4927 1.0000
6.250 1.0980 0.02046 0.01204 -0.0707 0.4743 1.0000
6.500 1.1231 0.02047 0.01208 -0.0700 0.4547 1.0000
6.750 1.1467 0.02016 0.01176 -0.0690 0.4289 1.0000
7.000 1.1697 0.02020 0.01182 -0.0682 0.4029 1.0000
7.250 1.1920 0.02046 0.01204 -0.0674 0.3781 1.0000
7.500 1.2124 0.02095 0.01244 -0.0664 0.3512 1.0000
7.750 1.2322 0.02166 0.01304 -0.0654 0.3286 1.0000
8.000 1.2489 0.02255 0.01386 -0.0642 0.2969 1.0000
8.250 1.2657 0.02345 0.01475 -0.0630 0.2692 1.0000
8.500 1.2818 0.02439 0.01572 -0.0617 0.2365 1.0000
8.750 1.2955 0.02557 0.01683 -0.0603 0.1824 1.0000
9.000 1.2873 0.02876 0.01903 -0.0572 0.0728 1.0000
9.250 1.2903 0.03095 0.02104 -0.0548 0.0594 1.0000
9.500 1.2939 0.03274 0.02295 -0.0524 0.0554 1.0000
9.750 1.2945 0.03484 0.02518 -0.0501 0.0530 1.0000
10.000 1.2921 0.03737 0.02785 -0.0483 0.0513 1.0000
10.250 1.2892 0.04013 0.03077 -0.0470 0.0502 1.0000
10.500 1.2879 0.04289 0.03373 -0.0461 0.0491 1.0000
10.750 1.2857 0.04584 0.03684 -0.0453 0.0479 1.0000
11.000 1.2833 0.04889 0.04002 -0.0446 0.0465 1.0000
11.250 1.2816 0.05186 0.04313 -0.0439 0.0454 1.0000
11.500 1.2826 0.05451 0.04584 -0.0428 0.0445 1.0000
11.750 1.2893 0.05649 0.04785 -0.0411 0.0439 1.0000
12.000 1.3056 0.05758 0.04891 -0.0386 0.0432 1.0000
12.250 1.3350 0.05809 0.04941 -0.0355 0.0429 1.0000
12.500 1.3691 0.05930 0.05072 -0.0330 0.0424 1.0000
12.750 1.4195 0.06246 0.05394 -0.0315 0.0411 1.0000
13.000 1.4278 0.06536 0.05712 -0.0303 0.0413 1.0000
13.250 1.4253 0.06814 0.06022 -0.0292 0.0419 1.0000
13.500 1.4185 0.07148 0.06395 -0.0283 0.0427 1.0000
13.750 1.4073 0.07554 0.06840 -0.0278 0.0436 1.0000
14.000 1.3896 0.08032 0.07356 -0.0280 0.0444 1.0000
14.250 1.3711 0.08557 0.07915 -0.0288 0.0452 1.0000
14.500 1.3516 0.09121 0.08509 -0.0301 0.0459 1.0000
14.750 1.3312 0.09724 0.09140 -0.0321 0.0466 1.0000
15.000 1.3099 0.10367 0.09806 -0.0346 0.0472 1.0000
15.250 1.2878 0.11053 0.10514 -0.0378 0.0477 1.0000
15.500 1.2652 0.11800 0.11281 -0.0418 0.0482 1.0000
15.750 1.2419 0.12618 0.12118 -0.0467 0.0486 1.0000
16.000 1.2179 0.13525 0.13041 -0.0525 0.0491 1.0000
16.250 1.1961 0.14478 0.14006 -0.0586 0.0497 1.0000
16.500 1.1176 0.17455 0.16999 -0.0813 0.0531 1.0000
16.750 1.0991 0.18951 0.18487 -0.0889 0.0597 1.0000
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Polar data table (+)
Polar graphs
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