GOE 522 AIRFOIL (goe522-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 522 AIRFOIL (goe522-il) Reynolds number: 200,000 Max Cl/Cd: 57.09 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe522-il-200000.txt Download as CSV file: xf-goe522-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 522 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6724 0.08057 0.07565 -0.0893 0.9953 0.0552
-15.000 -0.7020 0.07155 0.06630 -0.0976 0.9923 0.0549
-14.750 -0.7144 0.06569 0.06022 -0.1028 0.9882 0.0548
-14.500 -0.7174 0.06106 0.05539 -0.1074 0.9839 0.0549
-14.250 -0.7108 0.05729 0.05146 -0.1119 0.9805 0.0550
-14.000 -0.7000 0.05391 0.04791 -0.1165 0.9778 0.0553
-13.750 -0.6985 0.05128 0.04516 -0.1178 0.9709 0.0556
-13.500 -0.6864 0.04863 0.04237 -0.1210 0.9668 0.0560
-13.250 -0.6665 0.04612 0.03969 -0.1250 0.9639 0.0564
-13.000 -0.6584 0.04438 0.03790 -0.1253 0.9564 0.0567
-12.750 -0.6329 0.04297 0.03652 -0.1272 0.9519 0.0572
-12.500 -0.6028 0.04134 0.03489 -0.1303 0.9489 0.0577
-12.250 -0.5830 0.03971 0.03325 -0.1323 0.9441 0.0582
-12.000 -0.5757 0.03814 0.03165 -0.1323 0.9357 0.0587
-11.750 -0.5501 0.03634 0.02981 -0.1354 0.9321 0.0593
-11.500 -0.5198 0.03448 0.02787 -0.1393 0.9296 0.0602
-11.250 -0.5280 0.03322 0.02654 -0.1366 0.9174 0.0607
-11.000 -0.5036 0.03159 0.02484 -0.1390 0.9136 0.0615
-10.750 -0.4767 0.02998 0.02318 -0.1417 0.9111 0.0626
-10.500 -0.5019 0.02961 0.02275 -0.1343 0.8971 0.0627
-10.250 -0.4759 0.02833 0.02145 -0.1357 0.8940 0.0642
-10.000 -0.4422 0.02712 0.02019 -0.1381 0.8921 0.0662
-9.750 -0.4620 0.02698 0.02000 -0.1305 0.8787 0.0667
-9.500 -0.4312 0.02590 0.01890 -0.1320 0.8757 0.0692
-9.250 -0.3949 0.02484 0.01780 -0.1342 0.8736 0.0735
-9.000 -0.3916 0.02442 0.01739 -0.1304 0.8648 0.0764
-8.750 -0.3728 0.02370 0.01665 -0.1293 0.8585 0.0828
-8.500 -0.3405 0.02276 0.01574 -0.1306 0.8555 0.0933
-8.250 -0.3024 0.02193 0.01493 -0.1327 0.8532 0.1073
-8.000 -0.2936 0.02177 0.01474 -0.1294 0.8443 0.1154
-7.750 -0.2653 0.02134 0.01426 -0.1294 0.8385 0.1249
-7.500 -0.2257 0.02081 0.01365 -0.1314 0.8352 0.1344
-7.250 -0.1847 0.02021 0.01302 -0.1338 0.8324 0.1426
-7.000 -0.1745 0.02016 0.01288 -0.1304 0.8227 0.1470
-6.750 -0.1451 0.01961 0.01236 -0.1307 0.8169 0.1526
-6.500 -0.1037 0.01909 0.01169 -0.1330 0.8130 0.1599
-6.250 -0.0867 0.01872 0.01138 -0.1310 0.8042 0.1649
-6.000 -0.0587 0.01830 0.01090 -0.1308 0.7966 0.1717
-5.750 -0.0205 0.01766 0.01026 -0.1327 0.7915 0.1802
-5.500 -0.0059 0.01747 0.01005 -0.1301 0.7808 0.1873
-5.250 0.0257 0.01694 0.00955 -0.1307 0.7734 0.1968
-5.000 0.0495 0.01663 0.00922 -0.1297 0.7637 0.2062
-4.750 0.0764 0.01627 0.00886 -0.1294 0.7538 0.2186
-4.500 0.1016 0.01601 0.00862 -0.1287 0.7432 0.2335
-4.250 0.1287 0.01578 0.00837 -0.1283 0.7323 0.2516
-4.000 0.1515 0.01568 0.00826 -0.1272 0.7203 0.2701
-3.750 0.1821 0.01557 0.00805 -0.1274 0.7097 0.2898
-3.500 0.2006 0.01554 0.00804 -0.1254 0.6963 0.3047
-3.250 0.2298 0.01550 0.00790 -0.1255 0.6854 0.3209
-3.000 0.2502 0.01557 0.00784 -0.1238 0.6726 0.3347
-2.750 0.2747 0.01555 0.00783 -0.1230 0.6616 0.3478
-2.500 0.2985 0.01557 0.00777 -0.1221 0.6509 0.3605
-2.250 0.3228 0.01564 0.00781 -0.1213 0.6412 0.3726
-2.000 0.3460 0.01566 0.00776 -0.1202 0.6317 0.3832
-1.750 0.3728 0.01573 0.00777 -0.1199 0.6234 0.3935
-1.500 0.3937 0.01581 0.00777 -0.1185 0.6144 0.4030
-1.250 0.4229 0.01584 0.00777 -0.1186 0.6072 0.4136
-1.000 0.4445 0.01597 0.00785 -0.1173 0.5998 0.4237
-0.750 0.4681 0.01598 0.00789 -0.1164 0.5929 0.4323
-0.500 0.4989 0.01610 0.00789 -0.1169 0.5871 0.4417
-0.250 0.5211 0.01620 0.00797 -0.1158 0.5808 0.4506
0.000 0.5436 0.01625 0.00807 -0.1148 0.5745 0.4599
0.250 0.5719 0.01637 0.00808 -0.1148 0.5688 0.4706
0.500 0.5988 0.01647 0.00820 -0.1146 0.5632 0.4808
0.750 0.6186 0.01658 0.00833 -0.1130 0.5572 0.4927
1.000 0.6423 0.01663 0.00839 -0.1122 0.5510 0.5045
1.250 0.6759 0.01685 0.00846 -0.1133 0.5450 0.5204
1.500 0.6905 0.01687 0.00866 -0.1107 0.5394 0.5333
1.750 0.7112 0.01695 0.00876 -0.1093 0.5336 0.5496
2.000 0.7376 0.01707 0.00883 -0.1090 0.5280 0.5684
2.250 0.7639 0.01722 0.00902 -0.1087 0.5226 0.5877
2.500 0.7786 0.01728 0.00922 -0.1062 0.5173 0.6068
2.750 0.7991 0.01736 0.00936 -0.1047 0.5122 0.6284
3.000 0.8247 0.01747 0.00949 -0.1043 0.5077 0.6524
3.250 0.8554 0.01769 0.00972 -0.1048 0.5031 0.6794
3.500 0.8661 0.01775 0.00997 -0.1015 0.4988 0.7060
3.750 0.8816 0.01781 0.01018 -0.0991 0.4941 0.7380
4.000 0.9019 0.01786 0.01036 -0.0975 0.4897 0.7803
4.250 0.9334 0.01796 0.01055 -0.0980 0.4854 0.8425
4.500 0.9931 0.01829 0.01105 -0.1046 0.4800 0.9356
4.750 1.0267 0.01858 0.01134 -0.1064 0.4746 1.0000
5.000 1.0445 0.01879 0.01147 -0.1047 0.4701 1.0000
5.250 1.0702 0.01901 0.01158 -0.1045 0.4658 1.0000
5.500 1.0948 0.01936 0.01184 -0.1041 0.4614 1.0000
5.750 1.0977 0.01959 0.01214 -0.0997 0.4568 1.0000
6.000 1.1099 0.01983 0.01236 -0.0970 0.4519 1.0000
6.250 1.1300 0.02002 0.01248 -0.0957 0.4472 1.0000
6.500 1.1594 0.02031 0.01264 -0.0962 0.4423 1.0000
6.750 1.1583 0.02064 0.01306 -0.0913 0.4373 1.0000
7.000 1.1686 0.02092 0.01335 -0.0885 0.4319 1.0000
7.250 1.1872 0.02113 0.01349 -0.0871 0.4269 1.0000
7.500 1.2074 0.02144 0.01374 -0.0860 0.4218 1.0000
7.750 1.2090 0.02190 0.01428 -0.0820 0.4160 1.0000
8.000 1.2208 0.02222 0.01459 -0.0797 0.4103 1.0000
8.250 1.2464 0.02243 0.01465 -0.0795 0.4048 1.0000
8.500 1.2443 0.02308 0.01543 -0.0752 0.3985 1.0000
8.750 1.2524 0.02356 0.01591 -0.0726 0.3919 1.0000
9.000 1.2760 0.02381 0.01601 -0.0721 0.3860 1.0000
9.250 1.2719 0.02470 0.01703 -0.0681 0.3786 1.0000
9.500 1.2823 0.02526 0.01755 -0.0660 0.3719 1.0000
9.750 1.2944 0.02589 0.01814 -0.0642 0.3651 1.0000
10.000 1.2977 0.02681 0.01911 -0.0615 0.3575 1.0000
10.250 1.3159 0.02728 0.01945 -0.0606 0.3512 1.0000
10.500 1.3178 0.02843 0.02068 -0.0580 0.3439 1.0000
10.750 1.3273 0.02929 0.02152 -0.0562 0.3376 1.0000
11.000 1.3449 0.02993 0.02205 -0.0554 0.3320 1.0000
11.250 1.3479 0.03120 0.02341 -0.0532 0.3259 1.0000
11.500 1.3592 0.03211 0.02429 -0.0519 0.3207 1.0000
11.750 1.3838 0.03251 0.02454 -0.0518 0.3163 1.0000
12.000 1.3870 0.03393 0.02609 -0.0499 0.3121 1.0000
12.250 1.3959 0.03509 0.02731 -0.0486 0.3079 1.0000
12.500 1.4102 0.03598 0.02818 -0.0478 0.3044 1.0000
12.750 1.4344 0.03641 0.02852 -0.0477 0.3013 1.0000
13.000 1.4484 0.03743 0.02957 -0.0469 0.2982 1.0000
13.250 1.4517 0.03901 0.03126 -0.0454 0.2951 1.0000
13.500 1.4599 0.04033 0.03264 -0.0442 0.2919 1.0000
13.750 1.4723 0.04139 0.03372 -0.0434 0.2889 1.0000
14.000 1.4913 0.04209 0.03440 -0.0431 0.2865 1.0000
14.250 1.5258 0.04201 0.03420 -0.0438 0.2839 1.0000
14.500 1.5211 0.04417 0.03653 -0.0420 0.2817 1.0000
14.750 1.5190 0.04629 0.03880 -0.0405 0.2793 1.0000
15.000 1.5220 0.04813 0.04073 -0.0395 0.2768 1.0000
15.250 1.5300 0.04965 0.04231 -0.0387 0.2747 1.0000
15.500 1.5434 0.05075 0.04343 -0.0383 0.2725 1.0000
15.750 1.5634 0.05141 0.04408 -0.0381 0.2705 1.0000
16.000 1.5936 0.05146 0.04408 -0.0384 0.2687 1.0000
16.250 1.6013 0.05317 0.04588 -0.0378 0.2672 1.0000
16.500 1.5808 0.05697 0.04991 -0.0361 0.2655 1.0000
16.750 1.5609 0.06104 0.05419 -0.0348 0.2637 1.0000
17.000 1.5374 0.06567 0.05901 -0.0338 0.2613 1.0000
17.250 1.5243 0.06949 0.06297 -0.0333 0.2589 1.0000
17.500 1.5293 0.07156 0.06509 -0.0331 0.2570 1.0000
17.750 1.5484 0.07221 0.06575 -0.0330 0.2554 1.0000
18.000 1.5844 0.07118 0.06466 -0.0331 0.2539 1.0000
18.250 1.5966 0.07265 0.06617 -0.0330 0.2518 1.0000
18.500 0.9451 0.17389 0.16858 -0.0610 0.2094 1.0000
18.750 0.9663 0.17361 0.16831 -0.0606 0.2073 1.0000
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