GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.09 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe574-il-1000000-n5.txt Download as CSV file: xf-goe574-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 574 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2201 0.09079 0.08913 -0.0660 0.9733 0.0037
-9.000 -0.2196 0.08712 0.08548 -0.0670 0.9682 0.0035
-8.750 -0.2370 0.08525 0.08365 -0.0625 0.9553 0.0034
-8.500 -0.2267 0.08092 0.07931 -0.0665 0.9215 0.0039
-8.000 -0.2883 0.01813 0.01446 -0.1164 0.8433 0.0045
-7.750 -0.2714 0.01583 0.01162 -0.1152 0.8126 0.0046
-7.500 -0.2564 0.01450 0.00993 -0.1131 0.7922 0.0048
-7.250 -0.2386 0.01367 0.00886 -0.1112 0.7745 0.0051
-7.000 -0.2194 0.01302 0.00799 -0.1096 0.7581 0.0054
-6.750 -0.1989 0.01256 0.00738 -0.1082 0.7423 0.0058
-6.500 -0.1785 0.01206 0.00669 -0.1067 0.7268 0.0061
-6.250 -0.1575 0.01161 0.00608 -0.1053 0.7119 0.0066
-6.000 -0.1360 0.01123 0.00553 -0.1040 0.6969 0.0069
-5.750 -0.1141 0.01088 0.00505 -0.1028 0.6818 0.0078
-5.500 -0.0915 0.01062 0.00470 -0.1018 0.6664 0.0088
-5.250 -0.0688 0.01036 0.00430 -0.1007 0.6516 0.0098
-5.000 -0.0455 0.01014 0.00398 -0.0998 0.6368 0.0114
-4.750 -0.0198 0.01022 0.00403 -0.0993 0.6219 0.0132
-4.500 0.0051 0.01020 0.00393 -0.0987 0.6073 0.0149
-4.250 0.0297 0.01014 0.00377 -0.0981 0.5917 0.0160
-4.000 0.0564 0.01036 0.00396 -0.0979 0.5759 0.0172
-3.750 0.0820 0.01044 0.00396 -0.0975 0.5609 0.0186
-3.500 0.1068 0.01040 0.00382 -0.0969 0.5452 0.0201
-3.250 0.1321 0.01042 0.00375 -0.0964 0.5314 0.0216
-3.000 0.1573 0.01042 0.00367 -0.0959 0.5184 0.0227
-2.750 0.1824 0.01041 0.00357 -0.0953 0.5064 0.0232
-2.500 0.2080 0.01049 0.00359 -0.0949 0.4952 0.0237
-2.250 0.2310 0.01017 0.00316 -0.0940 0.4852 0.0246
-2.000 0.2534 0.00981 0.00274 -0.0929 0.4771 0.0258
-1.500 0.3010 0.00952 0.00233 -0.0912 0.4629 0.0269
-1.250 0.3249 0.00942 0.00217 -0.0904 0.4564 0.0271
-1.000 0.3489 0.00933 0.00203 -0.0896 0.4511 0.0273
-0.750 0.3731 0.00925 0.00191 -0.0889 0.4458 0.0275
-0.250 0.4213 0.00914 0.00172 -0.0873 0.4371 0.0281
0.000 0.4455 0.00908 0.00164 -0.0866 0.4335 0.0280
0.250 0.4697 0.00905 0.00158 -0.0858 0.4300 0.0279
0.500 0.4938 0.00903 0.00154 -0.0851 0.4267 0.0278
0.750 0.5180 0.00901 0.00150 -0.0844 0.4240 0.0279
1.000 0.5425 0.00900 0.00147 -0.0837 0.4214 0.0280
1.250 0.5668 0.00898 0.00145 -0.0830 0.4190 0.0284
1.500 0.5911 0.00899 0.00145 -0.0823 0.4164 0.0292
1.750 0.6153 0.00901 0.00146 -0.0816 0.4140 0.0299
2.000 0.6392 0.00903 0.00148 -0.0808 0.4115 0.0331
2.250 0.6625 0.00897 0.00154 -0.0799 0.4094 0.0857
2.500 0.6782 0.00844 0.00170 -0.0776 0.4073 0.3884
3.000 0.8633 0.00811 0.00276 -0.1084 0.3947 0.9925
3.250 0.9247 0.00827 0.00289 -0.1163 0.3873 0.9977
3.500 0.9697 0.00838 0.00296 -0.1206 0.3777 1.0000
3.750 0.9916 0.00847 0.00305 -0.1194 0.3714 1.0000
4.000 1.0129 0.00859 0.00315 -0.1181 0.3608 1.0000
4.250 1.0333 0.00875 0.00325 -0.1167 0.3455 1.0000
4.500 1.0411 0.00964 0.00364 -0.1129 0.2536 1.0000
4.750 1.0454 0.01068 0.00425 -0.1084 0.1722 1.0000
5.000 1.0397 0.01215 0.00515 -0.1019 0.0436 1.0000
5.250 1.0533 0.01257 0.00548 -0.0990 0.0161 1.0000
5.500 1.0696 0.01283 0.00574 -0.0968 0.0125 1.0000
5.750 1.0856 0.01309 0.00605 -0.0944 0.0100 1.0000
6.000 1.1005 0.01332 0.00631 -0.0919 0.0094 1.0000
6.250 1.1140 0.01353 0.00656 -0.0890 0.0085 1.0000
6.500 1.1267 0.01378 0.00684 -0.0860 0.0078 1.0000
6.750 1.1387 0.01408 0.00715 -0.0829 0.0068 1.0000
7.000 1.1500 0.01443 0.00755 -0.0796 0.0061 1.0000
7.250 1.1634 0.01473 0.00788 -0.0769 0.0057 1.0000
7.500 1.1763 0.01508 0.00827 -0.0741 0.0053 1.0000
7.750 1.1884 0.01547 0.00872 -0.0712 0.0050 1.0000
8.000 1.2012 0.01586 0.00914 -0.0685 0.0046 1.0000
8.250 1.2125 0.01634 0.00965 -0.0656 0.0044 1.0000
8.500 1.2228 0.01686 0.01022 -0.0625 0.0039 1.0000
8.750 1.2334 0.01741 0.01083 -0.0596 0.0038 1.0000
9.000 1.2429 0.01802 0.01151 -0.0566 0.0036 1.0000
9.250 1.2509 0.01874 0.01230 -0.0534 0.0035 1.0000
9.500 1.2625 0.01930 0.01290 -0.0510 0.0032 1.0000
9.750 1.2668 0.02025 0.01395 -0.0475 0.0031 1.0000
10.000 1.2824 0.02067 0.01439 -0.0460 0.0028 1.0000
10.250 1.2788 0.02214 0.01600 -0.0416 0.0030 1.0000
10.500 1.2940 0.02264 0.01650 -0.0403 0.0027 1.0000
10.750 1.2973 0.02388 0.01782 -0.0375 0.0026 1.0000
11.000 1.2877 0.02613 0.02020 -0.0337 0.0024 1.0000
11.250 1.2910 0.02768 0.02183 -0.0316 0.0024 1.0000
11.500 1.2935 0.02943 0.02368 -0.0298 0.0024 1.0000
11.750 1.2930 0.03156 0.02592 -0.0281 0.0023 1.0000
12.000 1.2897 0.03408 0.02855 -0.0264 0.0023 1.0000
12.250 1.2847 0.03688 0.03146 -0.0250 0.0023 1.0000
12.500 1.2846 0.03931 0.03399 -0.0240 0.0022 1.0000
12.750 1.2832 0.04195 0.03673 -0.0231 0.0022 1.0000
13.000 1.2907 0.04375 0.03860 -0.0227 0.0020 1.0000
13.250 1.2822 0.04718 0.04215 -0.0216 0.0021 1.0000
13.500 1.2773 0.05026 0.04535 -0.0207 0.0020 1.0000
13.750 1.2798 0.05269 0.04786 -0.0204 0.0019 1.0000
14.000 1.2785 0.05550 0.05079 -0.0198 0.0019 1.0000
14.250 1.2728 0.05865 0.05409 -0.0185 0.0019 1.0000
14.500 1.2785 0.06100 0.05650 -0.0190 0.0018 1.0000
14.750 1.2781 0.06387 0.05946 -0.0187 0.0017 1.0000
15.000 1.2805 0.06659 0.06227 -0.0190 0.0017 1.0000
15.250 1.2770 0.06982 0.06562 -0.0185 0.0016 1.0000
15.500 1.2774 0.07281 0.06870 -0.0187 0.0016 1.0000
15.750 1.2671 0.07671 0.07284 -0.0172 0.0016 1.0000
16.000 1.2731 0.07948 0.07561 -0.0190 0.0016 1.0000
16.250 1.2668 0.08334 0.07962 -0.0190 0.0016 1.0000
16.500 1.2685 0.08656 0.08289 -0.0203 0.0015 1.0000
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Polar data table (+)
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