GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 200,000 Max Cl/Cd: 73.45 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe478-il-200000.txt Download as CSV file: xf-goe478-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2103 0.08981 0.08617 -0.0658 0.9724 0.0796
-8.250 -0.1884 0.08639 0.08275 -0.0697 0.9684 0.0819
-8.000 -0.2169 0.07672 0.07305 -0.0917 0.9491 0.0870
-7.750 -0.1843 0.07491 0.07127 -0.0883 0.9485 0.0877
-7.500 -0.1551 0.07261 0.06896 -0.0885 0.9461 0.0890
-7.250 -0.1299 0.06924 0.06557 -0.0929 0.9428 0.0911
-7.000 -0.1407 0.05931 0.05535 -0.1107 0.9278 0.0982
-6.750 -0.1088 0.05714 0.05324 -0.1116 0.9260 0.0993
-6.500 -0.0926 0.05559 0.05170 -0.1107 0.9183 0.1010
-6.250 -0.1568 0.03422 0.02855 -0.1148 0.9004 0.0695
-6.000 -0.1332 0.03170 0.02588 -0.1150 0.8957 0.0679
-5.750 -0.1087 0.02865 0.02249 -0.1156 0.8920 0.0667
-5.500 -0.0986 0.02661 0.02011 -0.1129 0.8840 0.0659
-5.250 -0.0766 0.02477 0.01792 -0.1121 0.8786 0.0664
-5.000 -0.0475 0.02309 0.01588 -0.1124 0.8747 0.0673
-4.750 -0.0268 0.02198 0.01450 -0.1109 0.8687 0.0679
-4.500 -0.0045 0.02103 0.01332 -0.1097 0.8630 0.0684
-4.250 0.0241 0.01998 0.01207 -0.1097 0.8588 0.0694
-4.000 0.0566 0.01900 0.01108 -0.1104 0.8555 0.0710
-3.750 0.0761 0.01862 0.01071 -0.1087 0.8490 0.0726
-3.500 0.1017 0.01817 0.01019 -0.1081 0.8437 0.0753
-3.250 0.1319 0.01752 0.00946 -0.1082 0.8395 0.0782
-3.000 0.1606 0.01702 0.00901 -0.1081 0.8349 0.0814
-2.750 0.1813 0.01673 0.00872 -0.1065 0.8278 0.0851
-2.500 0.2091 0.01622 0.00824 -0.1061 0.8226 0.0901
-2.250 0.2411 0.01578 0.00777 -0.1065 0.8185 0.0988
-2.000 0.2597 0.01559 0.00764 -0.1046 0.8107 0.1089
-1.750 0.2853 0.01497 0.00718 -0.1038 0.8045 0.1301
-1.500 0.3157 0.01461 0.00692 -0.1040 0.7992 0.1650
-1.250 0.3361 0.01454 0.00694 -0.1023 0.7906 0.1890
-1.000 0.3655 0.01429 0.00672 -0.1023 0.7844 0.2145
-0.750 0.3898 0.01410 0.00658 -0.1013 0.7768 0.2401
-0.500 0.4141 0.01376 0.00638 -0.1004 0.7685 0.2720
-0.250 0.4400 0.01330 0.00618 -0.0998 0.7612 0.3327
0.000 0.4499 0.01231 0.00622 -0.0960 0.7512 0.5973
0.250 0.5690 0.01162 0.00621 -0.1126 0.7449 0.9747
0.500 0.6396 0.01156 0.00603 -0.1212 0.7328 1.0000
0.750 0.6615 0.01157 0.00591 -0.1198 0.7222 1.0000
1.000 0.6824 0.01157 0.00580 -0.1181 0.7102 1.0000
1.250 0.7010 0.01161 0.00578 -0.1161 0.6973 1.0000
1.500 0.7230 0.01164 0.00569 -0.1146 0.6855 1.0000
1.750 0.7433 0.01167 0.00562 -0.1129 0.6725 1.0000
2.000 0.7619 0.01173 0.00564 -0.1108 0.6585 1.0000
2.250 0.7823 0.01179 0.00562 -0.1091 0.6457 1.0000
2.500 0.8041 0.01185 0.00556 -0.1076 0.6339 1.0000
2.750 0.8239 0.01193 0.00558 -0.1059 0.6208 1.0000
3.000 0.8440 0.01204 0.00562 -0.1041 0.6081 1.0000
3.250 0.8647 0.01215 0.00563 -0.1025 0.5952 1.0000
3.500 0.8858 0.01228 0.00563 -0.1009 0.5825 1.0000
3.750 0.9064 0.01247 0.00571 -0.0993 0.5702 1.0000
4.000 0.9272 0.01269 0.00587 -0.0977 0.5592 1.0000
4.250 0.9505 0.01296 0.00600 -0.0967 0.5494 1.0000
4.500 0.9707 0.01322 0.00623 -0.0951 0.5389 1.0000
4.750 0.9936 0.01353 0.00644 -0.0940 0.5297 1.0000
5.000 1.0144 0.01381 0.00669 -0.0926 0.5201 1.0000
5.250 1.0369 0.01413 0.00695 -0.0915 0.5113 1.0000
5.500 1.0575 0.01441 0.00722 -0.0900 0.5024 1.0000
5.750 1.0804 0.01475 0.00751 -0.0890 0.4941 1.0000
6.000 1.0996 0.01501 0.00780 -0.0873 0.4852 1.0000
6.250 1.1223 0.01535 0.00807 -0.0862 0.4768 1.0000
6.500 1.1396 0.01558 0.00836 -0.0841 0.4673 1.0000
6.750 1.1594 0.01587 0.00861 -0.0825 0.4575 1.0000
7.000 1.1750 0.01607 0.00883 -0.0801 0.4463 1.0000
7.250 1.1901 0.01629 0.00907 -0.0776 0.4348 1.0000
7.500 1.2062 0.01654 0.00927 -0.0753 0.4235 1.0000
7.750 1.2185 0.01674 0.00953 -0.0724 0.4114 1.0000
8.000 1.2316 0.01700 0.00981 -0.0696 0.3996 1.0000
8.250 1.2428 0.01728 0.01006 -0.0665 0.3878 1.0000
8.500 1.2506 0.01756 0.01036 -0.0627 0.3744 1.0000
8.750 1.2583 0.01791 0.01072 -0.0591 0.3596 1.0000
9.000 1.2656 0.01833 0.01113 -0.0556 0.3434 1.0000
9.250 1.2720 0.01886 0.01162 -0.0521 0.3257 1.0000
9.500 1.2765 0.01954 0.01221 -0.0486 0.3065 1.0000
9.750 1.2811 0.02033 0.01294 -0.0452 0.2860 1.0000
10.000 1.2848 0.02127 0.01380 -0.0420 0.2666 1.0000
10.250 1.2884 0.02233 0.01476 -0.0390 0.2492 1.0000
10.500 1.2922 0.02348 0.01583 -0.0362 0.2336 1.0000
10.750 1.2966 0.02469 0.01697 -0.0336 0.2199 1.0000
11.000 1.3006 0.02598 0.01821 -0.0312 0.2078 1.0000
11.250 1.3046 0.02735 0.01951 -0.0289 0.1963 1.0000
11.500 1.3107 0.02864 0.02082 -0.0269 0.1851 1.0000
11.750 1.3151 0.03010 0.02225 -0.0250 0.1750 1.0000
12.000 1.3175 0.03174 0.02382 -0.0230 0.1658 1.0000
12.250 1.3230 0.03323 0.02537 -0.0214 0.1562 1.0000
12.500 1.3255 0.03500 0.02709 -0.0197 0.1482 1.0000
12.750 1.3296 0.03668 0.02879 -0.0182 0.1406 1.0000
13.000 1.3331 0.03848 0.03057 -0.0167 0.1341 1.0000
13.250 1.3378 0.04022 0.03234 -0.0155 0.1280 1.0000
13.500 1.3416 0.04207 0.03413 -0.0141 0.1230 1.0000
13.750 1.3476 0.04379 0.03595 -0.0131 0.1181 1.0000
14.000 1.3530 0.04557 0.03772 -0.0121 0.1143 1.0000
14.250 1.3610 0.04719 0.03930 -0.0110 0.1107 1.0000
14.500 1.3680 0.04892 0.04114 -0.0102 0.1076 1.0000
14.750 1.3751 0.05065 0.04292 -0.0094 0.1047 1.0000
15.000 1.3836 0.05226 0.04450 -0.0086 0.1020 1.0000
15.250 1.3955 0.05364 0.04588 -0.0077 0.0995 1.0000
15.500 1.4009 0.05563 0.04802 -0.0071 0.0974 1.0000
15.750 1.4076 0.05750 0.04999 -0.0066 0.0952 1.0000
16.000 1.4152 0.05929 0.05182 -0.0061 0.0932 1.0000
16.250 1.4266 0.06072 0.05321 -0.0055 0.0911 1.0000
16.500 1.4381 0.06227 0.05479 -0.0049 0.0891 1.0000
16.750 1.4387 0.06485 0.05757 -0.0046 0.0876 1.0000
17.000 1.4408 0.06733 0.06019 -0.0045 0.0859 1.0000
17.250 1.4444 0.06966 0.06260 -0.0044 0.0841 1.0000
17.500 1.4519 0.07153 0.06447 -0.0043 0.0823 1.0000
17.750 1.4686 0.07253 0.06539 -0.0036 0.0801 1.0000
18.000 1.4618 0.07613 0.06923 -0.0041 0.0790 1.0000
18.250 1.4574 0.07959 0.07289 -0.0046 0.0778 1.0000
18.500 1.4538 0.08301 0.07647 -0.0052 0.0763 1.0000
18.750 1.4539 0.08598 0.07953 -0.0058 0.0749 1.0000
19.000 1.4596 0.08818 0.08176 -0.0061 0.0734 1.0000
19.250 1.4778 0.08883 0.08230 -0.0054 0.0714 1.0000
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