GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 200,000 Max Cl/Cd: 73.04 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe553-il-200000.txt Download as CSV file: xf-goe553-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2633 0.09342 0.09006 -0.0402 1.0000 0.0671
-8.750 -0.2728 0.09100 0.08774 -0.0403 1.0000 0.0695
-8.500 -0.3174 0.08326 0.08017 -0.0566 0.9883 0.0718
-8.250 -0.2766 0.08245 0.07934 -0.0487 0.9902 0.0731
-8.000 -0.2436 0.07949 0.07636 -0.0517 0.9832 0.0753
-7.750 -0.2441 0.06395 0.06061 -0.0866 0.9506 0.0830
-7.500 -0.2069 0.06323 0.06005 -0.0821 0.9434 0.0842
-7.250 -0.1726 0.06170 0.05851 -0.0823 0.9298 0.0865
-7.000 -0.1631 0.05034 0.04655 -0.1042 0.8974 0.0960
-6.750 -0.1327 0.04837 0.04466 -0.1041 0.8775 0.0979
-6.500 -0.1030 0.03377 0.02986 -0.0984 0.8099 0.1070
-6.250 -0.0989 0.02886 0.02471 -0.1003 0.7966 0.1110
-6.000 -0.0800 0.02707 0.02289 -0.0996 0.7847 0.1135
-5.750 -0.0637 0.02480 0.02045 -0.1001 0.7725 0.1187
-5.500 -0.0489 0.02761 0.02104 -0.1101 0.7872 0.0714
-5.250 -0.0262 0.02504 0.01829 -0.1098 0.7747 0.0701
-5.000 -0.0017 0.02307 0.01602 -0.1095 0.7639 0.0684
-4.750 0.0237 0.02130 0.01387 -0.1090 0.7535 0.0665
-4.500 0.0498 0.01996 0.01223 -0.1084 0.7434 0.0656
-4.250 0.0766 0.01897 0.01097 -0.1079 0.7344 0.0656
-4.000 0.1029 0.01824 0.01012 -0.1075 0.7247 0.0666
-3.750 0.1300 0.01765 0.00937 -0.1070 0.7165 0.0681
-3.500 0.1564 0.01704 0.00868 -0.1065 0.7074 0.0692
-3.250 0.1834 0.01650 0.00801 -0.1061 0.6997 0.0701
-3.000 0.2099 0.01605 0.00750 -0.1056 0.6913 0.0713
-2.750 0.2360 0.01545 0.00689 -0.1051 0.6837 0.0730
-2.500 0.2624 0.01510 0.00656 -0.1047 0.6760 0.0761
-2.250 0.2891 0.01485 0.00629 -0.1043 0.6681 0.0805
-2.000 0.3160 0.01455 0.00596 -0.1040 0.6611 0.0854
-1.750 0.3427 0.01433 0.00573 -0.1036 0.6528 0.0935
-1.500 0.3701 0.01399 0.00541 -0.1034 0.6462 0.1168
-1.250 0.3909 0.01259 0.00546 -0.1028 0.6386 0.4971
-1.000 0.4167 0.01263 0.00558 -0.1020 0.6312 0.5712
-0.750 0.4428 0.01275 0.00569 -0.1013 0.6238 0.6116
-0.500 0.4683 0.01280 0.00578 -0.1004 0.6157 0.6451
-0.250 0.4944 0.01291 0.00585 -0.0996 0.6092 0.6733
0.000 0.5188 0.01293 0.00597 -0.0985 0.6008 0.7042
0.250 0.5434 0.01297 0.00601 -0.0974 0.5941 0.7380
0.500 0.5675 0.01297 0.00609 -0.0962 0.5861 0.7656
0.750 0.5929 0.01293 0.00604 -0.0954 0.5784 0.7871
1.000 0.6180 0.01290 0.00604 -0.0946 0.5709 0.8098
1.250 0.6427 0.01280 0.00601 -0.0937 0.5628 0.8381
1.500 0.6702 0.01269 0.00594 -0.0932 0.5562 0.8845
1.750 0.7146 0.01260 0.00590 -0.0966 0.5460 1.0000
2.000 0.7441 0.01275 0.00588 -0.0971 0.5383 1.0000
2.250 0.7716 0.01284 0.00591 -0.0971 0.5288 1.0000
2.500 0.7995 0.01299 0.00592 -0.0971 0.5210 1.0000
2.750 0.8263 0.01312 0.00600 -0.0969 0.5121 1.0000
3.000 0.8538 0.01330 0.00605 -0.0968 0.5052 1.0000
3.250 0.8801 0.01345 0.00620 -0.0965 0.4966 1.0000
3.500 0.9076 0.01365 0.00625 -0.0964 0.4901 1.0000
3.750 0.9332 0.01383 0.00647 -0.0960 0.4817 1.0000
4.000 0.9602 0.01404 0.00656 -0.0958 0.4750 1.0000
4.250 0.9860 0.01427 0.00680 -0.0954 0.4676 1.0000
4.500 1.0123 0.01448 0.00697 -0.0951 0.4606 1.0000
4.750 1.0383 0.01474 0.00718 -0.0948 0.4537 1.0000
5.000 1.0638 0.01496 0.00739 -0.0943 0.4461 1.0000
5.250 1.0901 0.01524 0.00759 -0.0941 0.4397 1.0000
5.500 1.1147 0.01548 0.00789 -0.0935 0.4324 1.0000
5.750 1.1408 0.01576 0.00810 -0.0932 0.4264 1.0000
6.000 1.1659 0.01608 0.00846 -0.0928 0.4203 1.0000
6.250 1.1907 0.01636 0.00876 -0.0923 0.4140 1.0000
6.500 1.2171 0.01671 0.00902 -0.0921 0.4086 1.0000
6.750 1.2405 0.01702 0.00945 -0.0914 0.4022 1.0000
7.000 1.2650 0.01732 0.00976 -0.0909 0.3961 1.0000
7.250 1.2904 0.01770 0.01010 -0.0906 0.3904 1.0000
7.500 1.3128 0.01801 0.01053 -0.0898 0.3837 1.0000
7.750 1.3371 0.01834 0.01083 -0.0892 0.3776 1.0000
8.000 1.3594 0.01870 0.01127 -0.0884 0.3707 1.0000
8.250 1.3811 0.01898 0.01158 -0.0874 0.3628 1.0000
8.500 1.4019 0.01932 0.01196 -0.0864 0.3545 1.0000
8.750 1.4221 0.01962 0.01227 -0.0852 0.3460 1.0000
9.000 1.4415 0.02000 0.01272 -0.0839 0.3378 1.0000
9.250 1.4606 0.02036 0.01309 -0.0826 0.3294 1.0000
9.500 1.4774 0.02077 0.01359 -0.0810 0.3203 1.0000
9.750 1.4950 0.02120 0.01397 -0.0795 0.3117 1.0000
10.000 1.5085 0.02164 0.01456 -0.0774 0.3021 1.0000
10.250 1.5231 0.02217 0.01506 -0.0755 0.2938 1.0000
10.500 1.5333 0.02267 0.01567 -0.0729 0.2850 1.0000
10.750 1.5438 0.02328 0.01628 -0.0704 0.2773 1.0000
11.000 1.5524 0.02391 0.01700 -0.0678 0.2691 1.0000
11.250 1.5609 0.02465 0.01776 -0.0653 0.2615 1.0000
11.500 1.5688 0.02544 0.01863 -0.0630 0.2540 1.0000
11.750 1.5765 0.02634 0.01955 -0.0608 0.2475 1.0000
12.000 1.5832 0.02731 0.02063 -0.0587 0.2402 1.0000
12.250 1.5889 0.02844 0.02175 -0.0566 0.2341 1.0000
12.500 1.5939 0.02966 0.02310 -0.0548 0.2266 1.0000
12.750 1.5952 0.03116 0.02460 -0.0528 0.2193 1.0000
13.000 1.5975 0.03277 0.02632 -0.0513 0.2113 1.0000
13.250 1.5973 0.03466 0.02824 -0.0498 0.2041 1.0000
13.500 1.5966 0.03677 0.03043 -0.0487 0.1960 1.0000
13.750 1.5943 0.03914 0.03286 -0.0477 0.1884 1.0000
14.000 1.5904 0.04180 0.03555 -0.0469 0.1806 1.0000
14.250 1.5859 0.04466 0.03850 -0.0464 0.1724 1.0000
14.500 1.5768 0.04807 0.04188 -0.0460 0.1642 1.0000
14.750 1.5703 0.05147 0.04543 -0.0459 0.1547 1.0000
15.000 1.5598 0.05542 0.04944 -0.0461 0.1447 1.0000
15.250 1.5475 0.05980 0.05388 -0.0466 0.1335 1.0000
15.500 1.5349 0.06446 0.05860 -0.0474 0.1202 1.0000
15.750 1.5200 0.06959 0.06372 -0.0485 0.1078 1.0000
16.000 1.5034 0.07514 0.06925 -0.0498 0.0994 1.0000
16.250 1.4877 0.08071 0.07481 -0.0513 0.0931 1.0000
16.500 1.4729 0.08627 0.08038 -0.0528 0.0885 1.0000
16.750 1.4615 0.09144 0.08559 -0.0543 0.0842 1.0000
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