GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 474 AIRFOIL (goe474-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.03 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe474-il-1000000-n5.txt Download as CSV file: xf-goe474-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 474 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7163 0.06500 0.06326 -0.0414 1.0000 0.0039
-10.750 -0.7504 0.05489 0.05306 -0.0497 1.0000 0.0037
-10.500 -0.8065 0.03658 0.03427 -0.0586 1.0000 0.0036
-10.250 -0.7960 0.02578 0.02286 -0.0644 0.9966 0.0036
-10.000 -0.7725 0.02282 0.01959 -0.0661 0.9941 0.0037
-9.750 -0.7498 0.02016 0.01661 -0.0671 0.9907 0.0038
-9.500 -0.7226 0.01849 0.01473 -0.0682 0.9881 0.0040
-9.250 -0.6937 0.01731 0.01338 -0.0693 0.9856 0.0042
-9.000 -0.6671 0.01639 0.01232 -0.0696 0.9813 0.0043
-8.750 -0.6381 0.01546 0.01124 -0.0704 0.9783 0.0045
-8.500 -0.6078 0.01466 0.01032 -0.0714 0.9760 0.0047
-8.250 -0.5808 0.01392 0.00945 -0.0715 0.9711 0.0049
-8.000 -0.5506 0.01324 0.00865 -0.0723 0.9675 0.0051
-7.750 -0.5203 0.01259 0.00788 -0.0731 0.9638 0.0053
-7.500 -0.4910 0.01211 0.00730 -0.0736 0.9579 0.0055
-7.250 -0.4604 0.01137 0.00645 -0.0744 0.9527 0.0062
-7.000 -0.4315 0.01093 0.00593 -0.0748 0.9457 0.0067
-6.750 -0.4017 0.01051 0.00542 -0.0753 0.9387 0.0072
-6.500 -0.3737 0.01013 0.00496 -0.0753 0.9300 0.0077
-6.250 -0.3457 0.00982 0.00456 -0.0754 0.9216 0.0081
-6.000 -0.3189 0.00942 0.00407 -0.0751 0.9126 0.0091
-5.750 -0.2921 0.00913 0.00374 -0.0749 0.9047 0.0103
-5.500 -0.2653 0.00889 0.00343 -0.0746 0.8966 0.0116
-5.250 -0.2388 0.00863 0.00313 -0.0743 0.8888 0.0136
-4.750 -0.1855 0.00826 0.00270 -0.0736 0.8729 0.0182
-4.500 -0.1590 0.00806 0.00245 -0.0733 0.8656 0.0218
-4.250 -0.1322 0.00790 0.00228 -0.0730 0.8582 0.0251
-4.000 -0.1053 0.00779 0.00211 -0.0727 0.8514 0.0270
-3.750 -0.0783 0.00770 0.00198 -0.0724 0.8442 0.0279
-3.500 -0.0515 0.00758 0.00180 -0.0721 0.8371 0.0294
-3.250 -0.0247 0.00743 0.00160 -0.0718 0.8295 0.0321
-3.000 0.0020 0.00730 0.00145 -0.0714 0.8225 0.0350
-2.750 0.0290 0.00719 0.00131 -0.0711 0.8154 0.0371
-2.500 0.0558 0.00709 0.00118 -0.0708 0.8086 0.0429
-2.250 0.0818 0.00686 0.00106 -0.0704 0.7990 0.0756
-2.000 0.1082 0.00678 0.00100 -0.0700 0.7869 0.0918
-1.750 0.1347 0.00675 0.00095 -0.0696 0.7738 0.1013
-1.500 0.1614 0.00673 0.00089 -0.0693 0.7625 0.1061
-1.250 0.1881 0.00670 0.00084 -0.0689 0.7515 0.1109
-1.000 0.2147 0.00671 0.00080 -0.0686 0.7371 0.1152
-0.750 0.2411 0.00672 0.00076 -0.0681 0.7209 0.1190
-0.500 0.2676 0.00672 0.00074 -0.0678 0.7068 0.1245
-0.250 0.2938 0.00675 0.00072 -0.0673 0.6876 0.1295
0.000 0.3193 0.00682 0.00071 -0.0667 0.6625 0.1346
0.250 0.3448 0.00690 0.00071 -0.0662 0.6357 0.1414
0.500 0.3709 0.00694 0.00073 -0.0657 0.6146 0.1515
0.750 0.3967 0.00699 0.00075 -0.0653 0.5924 0.1663
1.000 0.4219 0.00711 0.00079 -0.0647 0.5572 0.1781
1.250 0.4452 0.00738 0.00086 -0.0638 0.4919 0.1921
1.500 0.4679 0.00771 0.00099 -0.0629 0.4249 0.2138
1.750 0.4917 0.00789 0.00111 -0.0621 0.3809 0.2561
2.000 0.5129 0.00757 0.00126 -0.0611 0.3468 0.4931
2.250 0.5412 0.00665 0.00149 -0.0614 0.3098 0.9659
2.500 0.5891 0.00697 0.00164 -0.0661 0.2688 0.9896
2.750 0.6243 0.00727 0.00177 -0.0679 0.2327 0.9982
3.000 0.6533 0.00755 0.00192 -0.0683 0.2029 1.0000
3.250 0.6763 0.00777 0.00206 -0.0673 0.1831 1.0000
3.500 0.6997 0.00798 0.00220 -0.0664 0.1679 1.0000
3.750 0.7230 0.00820 0.00235 -0.0655 0.1522 1.0000
4.000 0.7465 0.00841 0.00251 -0.0646 0.1393 1.0000
4.250 0.7701 0.00862 0.00267 -0.0637 0.1285 1.0000
4.500 0.7938 0.00882 0.00284 -0.0629 0.1172 1.0000
4.750 0.8172 0.00905 0.00302 -0.0620 0.1050 1.0000
5.000 0.8405 0.00930 0.00322 -0.0611 0.0941 1.0000
5.250 0.8640 0.00954 0.00343 -0.0602 0.0859 1.0000
5.500 0.8872 0.00981 0.00365 -0.0594 0.0768 1.0000
5.750 0.9112 0.01001 0.00386 -0.0586 0.0715 1.0000
6.000 0.9342 0.01031 0.00412 -0.0577 0.0608 1.0000
6.250 0.9564 0.01069 0.00441 -0.0567 0.0445 1.0000
6.500 0.9779 0.01115 0.00478 -0.0556 0.0311 1.0000
6.750 0.9997 0.01159 0.00517 -0.0546 0.0200 1.0000
7.000 1.0218 0.01201 0.00556 -0.0535 0.0133 1.0000
7.250 1.0442 0.01240 0.00595 -0.0526 0.0107 1.0000
7.500 1.0664 0.01281 0.00639 -0.0516 0.0088 1.0000
7.750 1.0892 0.01316 0.00678 -0.0507 0.0081 1.0000
8.000 1.1114 0.01356 0.00721 -0.0498 0.0072 1.0000
8.250 1.1330 0.01403 0.00770 -0.0488 0.0065 1.0000
8.500 1.1543 0.01453 0.00825 -0.0477 0.0059 1.0000
8.750 1.1763 0.01492 0.00869 -0.0468 0.0055 1.0000
9.000 1.1977 0.01538 0.00919 -0.0457 0.0051 1.0000
9.250 1.2187 0.01587 0.00974 -0.0447 0.0047 1.0000
9.500 1.2388 0.01643 0.01035 -0.0435 0.0044 1.0000
9.750 1.2570 0.01719 0.01118 -0.0420 0.0040 1.0000
10.000 1.2769 0.01771 0.01177 -0.0408 0.0039 1.0000
10.250 1.2962 0.01828 0.01241 -0.0396 0.0038 1.0000
10.500 1.3140 0.01896 0.01317 -0.0381 0.0036 1.0000
10.750 1.3316 0.01962 0.01390 -0.0366 0.0035 1.0000
11.000 1.3480 0.02034 0.01471 -0.0350 0.0034 1.0000
11.250 1.3639 0.02105 0.01549 -0.0333 0.0032 1.0000
11.500 1.3780 0.02176 0.01627 -0.0313 0.0031 1.0000
11.750 1.3899 0.02250 0.01711 -0.0290 0.0030 1.0000
12.000 1.4011 0.02327 0.01795 -0.0266 0.0028 1.0000
12.250 1.4097 0.02423 0.01900 -0.0240 0.0027 1.0000
12.500 1.4121 0.02562 0.02051 -0.0207 0.0026 1.0000
12.750 1.4209 0.02658 0.02157 -0.0185 0.0025 1.0000
13.000 1.4264 0.02780 0.02291 -0.0160 0.0025 1.0000
13.250 1.4313 0.02910 0.02433 -0.0137 0.0024 1.0000
13.500 1.4350 0.03055 0.02590 -0.0116 0.0024 1.0000
13.750 1.4369 0.03222 0.02769 -0.0095 0.0023 1.0000
14.000 1.4380 0.03402 0.02963 -0.0077 0.0023 1.0000
14.250 1.4379 0.03605 0.03178 -0.0061 0.0023 1.0000
14.500 1.4372 0.03824 0.03409 -0.0049 0.0022 1.0000
14.750 1.4312 0.04112 0.03712 -0.0038 0.0022 1.0000
15.000 1.4253 0.04420 0.04035 -0.0033 0.0022 1.0000
15.250 1.4195 0.04750 0.04379 -0.0032 0.0021 1.0000
15.500 1.4124 0.05120 0.04762 -0.0037 0.0021 1.0000
15.750 1.3950 0.05663 0.05323 -0.0052 0.0021 1.0000
16.000 1.3770 0.06274 0.05950 -0.0076 0.0021 1.0000
16.250 1.3673 0.06808 0.06497 -0.0101 0.0020 1.0000
16.500 1.3415 0.07716 0.07423 -0.0153 0.0021 1.0000
16.750 1.3088 0.08847 0.08574 -0.0219 0.0021 1.0000
17.000 1.2735 0.10064 0.09807 -0.0287 0.0021 1.0000
17.250 1.2390 0.11269 0.11026 -0.0352 0.0022 1.0000
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