GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 423 AIRFOIL (goe423-il) Reynolds number: 200,000 Max Cl/Cd: 70.48 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe423-il-200000-n5.txt Download as CSV file: xf-goe423-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 423 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2261 0.11188 0.10772 -0.0816 0.9676 0.0478
-12.250 -0.2275 0.10635 0.10217 -0.0851 0.9610 0.0482
-12.000 -0.2409 0.09795 0.09374 -0.0906 0.9556 0.0492
-11.750 -0.2280 0.09610 0.09189 -0.0916 0.9470 0.0497
-11.500 -0.2180 0.09324 0.08901 -0.0935 0.9395 0.0502
-11.250 -0.2171 0.08937 0.08512 -0.0953 0.9290 0.0506
-11.000 -0.2209 0.08445 0.08019 -0.0980 0.9190 0.0509
-10.750 -0.4229 0.04533 0.04046 -0.1261 0.8951 0.0521
-10.500 -0.4491 0.04077 0.03548 -0.1242 0.8808 0.0526
-10.250 -0.4573 0.03726 0.03154 -0.1223 0.8688 0.0532
-10.000 -0.4563 0.03444 0.02829 -0.1206 0.8571 0.0537
-9.750 -0.4498 0.03215 0.02560 -0.1188 0.8451 0.0543
-9.500 -0.4387 0.03023 0.02324 -0.1173 0.8337 0.0549
-9.250 -0.4225 0.02879 0.02151 -0.1162 0.8215 0.0555
-9.000 -0.4020 0.02782 0.02045 -0.1155 0.8083 0.0560
-8.750 -0.3809 0.02695 0.01944 -0.1148 0.7946 0.0566
-8.500 -0.3599 0.02608 0.01839 -0.1140 0.7793 0.0571
-8.250 -0.3387 0.02521 0.01733 -0.1131 0.7621 0.0577
-8.000 -0.3174 0.02438 0.01628 -0.1123 0.7432 0.0583
-7.750 -0.2957 0.02361 0.01528 -0.1114 0.7236 0.0589
-7.500 -0.2736 0.02289 0.01433 -0.1106 0.7050 0.0596
-7.250 -0.2511 0.02226 0.01345 -0.1098 0.6893 0.0605
-6.750 -0.2047 0.02119 0.01189 -0.1083 0.6659 0.0621
-6.500 -0.1809 0.02058 0.01117 -0.1078 0.6573 0.0628
-6.250 -0.1565 0.02007 0.01060 -0.1074 0.6497 0.0635
-6.000 -0.1320 0.01964 0.01009 -0.1069 0.6431 0.0643
-5.750 -0.1071 0.01925 0.00962 -0.1065 0.6375 0.0651
-5.500 -0.0821 0.01886 0.00916 -0.1061 0.6320 0.0660
-5.250 -0.0570 0.01853 0.00873 -0.1057 0.6268 0.0672
-5.000 -0.0317 0.01824 0.00832 -0.1053 0.6223 0.0685
-4.750 -0.0060 0.01796 0.00794 -0.1049 0.6181 0.0697
-4.500 0.0190 0.01757 0.00757 -0.1045 0.6140 0.0709
-4.250 0.0442 0.01727 0.00726 -0.1041 0.6103 0.0722
-4.000 0.0696 0.01703 0.00698 -0.1038 0.6069 0.0736
-3.750 0.0954 0.01683 0.00672 -0.1035 0.6039 0.0752
-3.500 0.1214 0.01665 0.00647 -0.1032 0.6011 0.0770
-3.250 0.1471 0.01644 0.00625 -0.1029 0.5982 0.0792
-3.000 0.1725 0.01622 0.00607 -0.1026 0.5953 0.0818
-2.750 0.1985 0.01606 0.00591 -0.1023 0.5925 0.0850
-2.500 0.2246 0.01593 0.00575 -0.1020 0.5899 0.0884
-2.250 0.2505 0.01578 0.00562 -0.1017 0.5873 0.0930
-2.000 0.2770 0.01569 0.00551 -0.1016 0.5848 0.1000
-1.500 0.3295 0.01548 0.00543 -0.1012 0.5800 0.1298
-1.250 0.3555 0.01539 0.00540 -0.1010 0.5777 0.1497
-1.000 0.3816 0.01530 0.00537 -0.1007 0.5755 0.1693
-0.750 0.4072 0.01516 0.00537 -0.1005 0.5733 0.1969
-0.500 0.4325 0.01500 0.00539 -0.1002 0.5712 0.2474
-0.250 0.4577 0.01482 0.00541 -0.0999 0.5693 0.3084
0.000 0.4804 0.01445 0.00545 -0.0992 0.5675 0.4220
0.250 0.5017 0.01406 0.00557 -0.0980 0.5658 0.5803
0.500 0.5231 0.01370 0.00573 -0.0964 0.5642 0.7220
0.750 0.5771 0.01372 0.00617 -0.1010 0.5622 0.9055
1.000 0.6253 0.01392 0.00638 -0.1051 0.5600 0.9456
1.250 0.6640 0.01411 0.00655 -0.1074 0.5579 0.9658
1.500 0.7072 0.01431 0.00670 -0.1107 0.5560 0.9806
1.750 0.7532 0.01446 0.00682 -0.1148 0.5541 0.9902
2.000 0.7984 0.01460 0.00693 -0.1187 0.5523 0.9979
2.250 0.8283 0.01475 0.00704 -0.1194 0.5506 1.0000
2.500 0.8509 0.01489 0.00716 -0.1186 0.5489 1.0000
2.750 0.8739 0.01505 0.00727 -0.1179 0.5472 1.0000
3.000 0.8977 0.01522 0.00740 -0.1173 0.5456 1.0000
3.250 0.9217 0.01543 0.00758 -0.1167 0.5441 1.0000
3.500 0.9425 0.01563 0.00782 -0.1155 0.5425 1.0000
3.750 0.9634 0.01583 0.00806 -0.1144 0.5407 1.0000
4.000 0.9844 0.01603 0.00830 -0.1133 0.5386 1.0000
4.250 1.0058 0.01624 0.00854 -0.1122 0.5365 1.0000
4.500 1.0277 0.01644 0.00877 -0.1112 0.5345 1.0000
4.750 1.0497 0.01659 0.00891 -0.1102 0.5315 1.0000
5.000 1.0732 0.01665 0.00892 -0.1094 0.5277 1.0000
5.250 1.0909 0.01676 0.00905 -0.1075 0.5225 1.0000
5.500 1.1069 0.01683 0.00918 -0.1053 0.5164 1.0000
5.750 1.1269 0.01685 0.00917 -0.1038 0.5112 1.0000
6.000 1.1475 0.01694 0.00924 -0.1025 0.5064 1.0000
6.250 1.1625 0.01710 0.00950 -0.1002 0.5011 1.0000
6.500 1.1807 0.01722 0.00966 -0.0984 0.4963 1.0000
6.750 1.2017 0.01729 0.00969 -0.0972 0.4915 1.0000
7.000 1.2164 0.01748 0.00998 -0.0949 0.4856 1.0000
7.250 1.2320 0.01765 0.01021 -0.0928 0.4796 1.0000
7.500 1.2504 0.01774 0.01028 -0.0911 0.4740 1.0000
7.750 1.2612 0.01799 0.01065 -0.0881 0.4664 1.0000
8.000 1.2738 0.01817 0.01085 -0.0855 0.4590 1.0000
8.250 1.2851 0.01847 0.01123 -0.0828 0.4506 1.0000
8.500 1.2965 0.01876 0.01152 -0.0801 0.4408 1.0000
8.750 1.3054 0.01918 0.01199 -0.0772 0.4265 1.0000
9.000 1.3123 0.01972 0.01253 -0.0741 0.4054 1.0000
9.250 1.3134 0.02054 0.01322 -0.0703 0.3767 1.0000
9.500 1.3067 0.02190 0.01438 -0.0658 0.3443 1.0000
9.750 1.2968 0.02373 0.01603 -0.0614 0.3160 1.0000
10.000 1.2880 0.02578 0.01796 -0.0577 0.2905 1.0000
10.250 1.2775 0.02818 0.02025 -0.0542 0.2660 1.0000
10.500 1.2655 0.03091 0.02288 -0.0511 0.2396 1.0000
10.750 1.2539 0.03387 0.02574 -0.0485 0.2152 1.0000
11.000 1.2402 0.03724 0.02900 -0.0461 0.1865 1.0000
11.250 1.2130 0.04209 0.03358 -0.0435 0.1383 1.0000
11.500 1.1932 0.04645 0.03774 -0.0417 0.1069 1.0000
11.750 1.1791 0.05040 0.04153 -0.0402 0.0735 1.0000
12.000 1.1715 0.05378 0.04481 -0.0391 0.0602 1.0000
12.250 1.1717 0.05644 0.04747 -0.0383 0.0558 1.0000
12.500 1.1730 0.05904 0.05010 -0.0376 0.0531 1.0000
12.750 1.1765 0.06144 0.05257 -0.0371 0.0512 1.0000
13.000 1.1794 0.06392 0.05511 -0.0366 0.0497 1.0000
13.250 1.1812 0.06655 0.05780 -0.0361 0.0484 1.0000
13.500 1.1819 0.06935 0.06065 -0.0357 0.0473 1.0000
13.750 1.1845 0.07197 0.06334 -0.0354 0.0463 1.0000
14.000 1.1877 0.07454 0.06599 -0.0351 0.0454 1.0000
14.250 1.1903 0.07719 0.06872 -0.0348 0.0446 1.0000
14.500 1.1922 0.07996 0.07156 -0.0346 0.0438 1.0000
14.750 1.1942 0.08274 0.07441 -0.0345 0.0432 1.0000
15.000 1.1954 0.08564 0.07737 -0.0344 0.0426 1.0000
15.250 1.1966 0.08854 0.08033 -0.0344 0.0421 1.0000
15.500 1.1972 0.09150 0.08333 -0.0343 0.0416 1.0000
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