GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 500,000 Max Cl/Cd: 93.48 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe645-il-500000.txt Download as CSV file: xf-goe645-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6378 0.08891 0.08592 -0.0589 1.0000 0.0288
-15.000 -0.7021 0.07466 0.07141 -0.0688 1.0000 0.0286
-14.750 -0.7371 0.06622 0.06281 -0.0748 1.0000 0.0286
-14.500 -0.7649 0.05920 0.05563 -0.0798 1.0000 0.0287
-14.250 -0.7851 0.05341 0.04971 -0.0839 1.0000 0.0287
-14.000 -0.8035 0.04790 0.04405 -0.0880 1.0000 0.0289
-13.750 -0.8193 0.04279 0.03879 -0.0922 1.0000 0.0290
-13.500 -0.8354 0.03830 0.03412 -0.0962 1.0000 0.0292
-13.250 -0.8543 0.03577 0.03146 -0.0955 1.0000 0.0292
-13.000 -0.8743 0.03441 0.02999 -0.0910 1.0000 0.0293
-12.750 -0.8848 0.03234 0.02785 -0.0876 1.0000 0.0296
-12.500 -0.8877 0.03099 0.02649 -0.0844 1.0000 0.0300
-12.250 -0.8813 0.02993 0.02540 -0.0824 0.9995 0.0304
-12.000 -0.8469 0.02858 0.02400 -0.0855 0.9959 0.0310
-11.750 -0.8123 0.02729 0.02261 -0.0886 0.9921 0.0319
-11.500 -0.7799 0.02607 0.02125 -0.0909 0.9869 0.0328
-11.250 -0.7445 0.02500 0.01998 -0.0936 0.9829 0.0336
-11.000 -0.7168 0.02329 0.01818 -0.0950 0.9765 0.0345
-10.750 -0.6840 0.02214 0.01703 -0.0968 0.9713 0.0352
-10.500 -0.6520 0.02123 0.01608 -0.0982 0.9648 0.0361
-10.250 -0.6197 0.02038 0.01515 -0.0996 0.9574 0.0371
-10.000 -0.5853 0.01963 0.01429 -0.1013 0.9492 0.0382
-9.750 -0.5486 0.01878 0.01331 -0.1034 0.9409 0.0390
-9.500 -0.5158 0.01753 0.01205 -0.1051 0.9284 0.0402
-9.250 -0.4803 0.01678 0.01126 -0.1070 0.9142 0.0413
-9.000 -0.4475 0.01621 0.01058 -0.1081 0.8969 0.0426
-8.750 -0.4190 0.01575 0.00997 -0.1082 0.8782 0.0437
-8.500 -0.3928 0.01538 0.00946 -0.1078 0.8601 0.0445
-8.250 -0.3721 0.01459 0.00858 -0.1067 0.8428 0.0458
-8.000 -0.3488 0.01414 0.00805 -0.1058 0.8279 0.0471
-7.750 -0.3247 0.01379 0.00760 -0.1050 0.8146 0.0486
-7.500 -0.3004 0.01348 0.00718 -0.1041 0.8019 0.0500
-7.250 -0.2767 0.01306 0.00667 -0.1032 0.7899 0.0515
-7.000 -0.2533 0.01261 0.00615 -0.1023 0.7788 0.0536
-6.750 -0.2286 0.01229 0.00576 -0.1016 0.7677 0.0559
-6.500 -0.2036 0.01197 0.00536 -0.1008 0.7578 0.0590
-6.250 -0.1790 0.01160 0.00495 -0.1001 0.7476 0.0637
-6.000 -0.1541 0.01123 0.00461 -0.0994 0.7376 0.0738
-5.750 -0.1286 0.01097 0.00443 -0.0987 0.7276 0.1001
-5.500 -0.1022 0.01081 0.00427 -0.0982 0.7174 0.1146
-5.250 -0.0759 0.01069 0.00409 -0.0977 0.7078 0.1241
-5.000 -0.0492 0.01057 0.00393 -0.0972 0.6975 0.1314
-4.750 -0.0230 0.01043 0.00375 -0.0967 0.6874 0.1382
-4.500 0.0033 0.01032 0.00361 -0.0961 0.6762 0.1450
-4.250 0.0297 0.01019 0.00346 -0.0956 0.6652 0.1530
-4.000 0.0560 0.01012 0.00333 -0.0950 0.6543 0.1615
-3.750 0.0824 0.00998 0.00322 -0.0945 0.6424 0.1731
-3.500 0.1087 0.00990 0.00314 -0.0940 0.6307 0.1878
-3.250 0.1348 0.00985 0.00307 -0.0934 0.6183 0.2043
-3.000 0.1613 0.00982 0.00303 -0.0929 0.6051 0.2198
-2.750 0.1879 0.00982 0.00301 -0.0923 0.5920 0.2338
-2.500 0.2143 0.00987 0.00299 -0.0918 0.5788 0.2461
-2.250 0.2406 0.00995 0.00300 -0.0912 0.5658 0.2578
-2.000 0.2670 0.00997 0.00299 -0.0907 0.5531 0.2665
-1.750 0.2936 0.01003 0.00298 -0.0902 0.5407 0.2738
-1.500 0.3198 0.01009 0.00296 -0.0896 0.5291 0.2800
-1.250 0.3461 0.01012 0.00296 -0.0891 0.5184 0.2865
-1.000 0.3730 0.01018 0.00296 -0.0887 0.5094 0.2927
-0.750 0.3995 0.01022 0.00295 -0.0882 0.5009 0.2984
-0.500 0.4260 0.01024 0.00297 -0.0878 0.4930 0.3047
-0.250 0.4527 0.01030 0.00298 -0.0873 0.4848 0.3109
0.000 0.4789 0.01035 0.00299 -0.0868 0.4770 0.3172
0.250 0.5055 0.01036 0.00302 -0.0864 0.4693 0.3242
0.750 0.5583 0.01045 0.00308 -0.0855 0.4557 0.3393
1.000 0.5845 0.01051 0.00312 -0.0850 0.4489 0.3469
1.250 0.6106 0.01055 0.00316 -0.0845 0.4428 0.3549
1.500 0.6371 0.01058 0.00321 -0.0841 0.4364 0.3647
1.750 0.6626 0.01063 0.00327 -0.0835 0.4301 0.3764
2.000 0.6886 0.01066 0.00334 -0.0830 0.4242 0.3911
2.250 0.7144 0.01067 0.00341 -0.0825 0.4179 0.4086
2.500 0.7389 0.01072 0.00349 -0.0818 0.4116 0.4329
2.750 0.7639 0.01064 0.00359 -0.0811 0.4057 0.4799
3.000 0.7863 0.01046 0.00372 -0.0800 0.3994 0.5881
3.250 0.8629 0.00988 0.00402 -0.0903 0.3898 1.0000
3.500 0.8867 0.01001 0.00411 -0.0894 0.3830 1.0000
3.750 0.9094 0.01020 0.00422 -0.0883 0.3762 1.0000
4.000 0.9335 0.01032 0.00432 -0.0874 0.3684 1.0000
4.250 0.9557 0.01052 0.00445 -0.0863 0.3605 1.0000
4.500 0.9797 0.01066 0.00457 -0.0854 0.3529 1.0000
4.750 1.0017 0.01087 0.00471 -0.0842 0.3447 1.0000
5.000 1.0252 0.01103 0.00485 -0.0833 0.3367 1.0000
5.250 1.0468 0.01127 0.00502 -0.0821 0.3281 1.0000
5.500 1.0699 0.01145 0.00519 -0.0812 0.3202 1.0000
6.000 1.1134 0.01191 0.00558 -0.0788 0.3041 1.0000
6.500 1.1556 0.01242 0.00602 -0.0763 0.2894 1.0000
6.750 1.1755 0.01271 0.00627 -0.0749 0.2822 1.0000
7.000 1.1960 0.01298 0.00652 -0.0736 0.2761 1.0000
7.250 1.2161 0.01325 0.00678 -0.0722 0.2702 1.0000
7.500 1.2333 0.01358 0.00707 -0.0703 0.2650 1.0000
7.750 1.2520 0.01383 0.00733 -0.0687 0.2597 1.0000
8.000 1.2696 0.01412 0.00762 -0.0669 0.2551 1.0000
8.250 1.2856 0.01447 0.00795 -0.0649 0.2508 1.0000
8.500 1.3033 0.01478 0.00828 -0.0632 0.2469 1.0000
8.750 1.3217 0.01508 0.00860 -0.0616 0.2429 1.0000
9.000 1.3386 0.01543 0.00897 -0.0599 0.2388 1.0000
9.250 1.3536 0.01588 0.00940 -0.0580 0.2347 1.0000
9.500 1.3714 0.01623 0.00979 -0.0565 0.2313 1.0000
9.750 1.3888 0.01660 0.01020 -0.0550 0.2270 1.0000
10.000 1.4038 0.01709 0.01069 -0.0533 0.2222 1.0000
10.250 1.4174 0.01766 0.01126 -0.0514 0.2177 1.0000
10.500 1.4347 0.01809 0.01174 -0.0501 0.2131 1.0000
10.750 1.4483 0.01870 0.01237 -0.0485 0.2074 1.0000
11.000 1.4609 0.01940 0.01307 -0.0468 0.2015 1.0000
11.250 1.4748 0.02007 0.01376 -0.0453 0.1940 1.0000
11.500 1.4855 0.02094 0.01463 -0.0437 0.1860 1.0000
11.750 1.4953 0.02193 0.01561 -0.0421 0.1758 1.0000
12.000 1.5034 0.02309 0.01674 -0.0405 0.1632 1.0000
12.250 1.5069 0.02463 0.01822 -0.0388 0.1501 1.0000
12.500 1.5118 0.02617 0.01974 -0.0373 0.1436 1.0000
12.750 1.5164 0.02781 0.02139 -0.0361 0.1392 1.0000
13.000 1.5207 0.02954 0.02316 -0.0349 0.1358 1.0000
13.250 1.5257 0.03129 0.02496 -0.0340 0.1335 1.0000
13.500 1.5299 0.03315 0.02687 -0.0331 0.1316 1.0000
13.750 1.5325 0.03521 0.02898 -0.0323 0.1297 1.0000
14.000 1.5341 0.03741 0.03124 -0.0316 0.1282 1.0000
14.250 1.5342 0.03982 0.03370 -0.0310 0.1267 1.0000
14.500 1.5319 0.04252 0.03645 -0.0304 0.1247 1.0000
14.750 1.5350 0.04476 0.03878 -0.0301 0.1235 1.0000
15.000 1.5383 0.04703 0.04114 -0.0299 0.1222 1.0000
15.250 1.5391 0.04959 0.04379 -0.0297 0.1206 1.0000
15.500 1.5386 0.05236 0.04663 -0.0296 0.1193 1.0000
15.750 1.5373 0.05526 0.04961 -0.0295 0.1181 1.0000
16.000 1.5332 0.05849 0.05290 -0.0296 0.1165 1.0000
16.250 1.5301 0.06166 0.05612 -0.0297 0.1152 1.0000
16.500 1.5262 0.06491 0.05942 -0.0299 0.1136 1.0000
16.750 1.5243 0.06794 0.06251 -0.0300 0.1118 1.0000
17.000 1.5255 0.07080 0.06549 -0.0304 0.1106 1.0000
17.250 1.5252 0.07384 0.06863 -0.0309 0.1089 1.0000
17.500 1.5223 0.07725 0.07213 -0.0314 0.1067 1.0000
17.750 1.5182 0.08079 0.07574 -0.0321 0.1050 1.0000
18.000 1.5124 0.08453 0.07952 -0.0327 0.1031 1.0000
18.250 1.5072 0.08815 0.08317 -0.0333 0.1009 1.0000
18.500 1.5052 0.09163 0.08677 -0.0342 0.0991 1.0000
18.750 1.5043 0.09503 0.09029 -0.0351 0.0970 1.0000
19.000 1.4997 0.09896 0.09431 -0.0363 0.0938 1.0000
19.250 1.4907 0.10345 0.09885 -0.0376 0.0909 1.0000
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Polar data table (+)
Polar graphs
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