GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 50,000 Max Cl/Cd: 41.88 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe399-il-50000-n5.txt Download as CSV file: xf-goe399-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3494 0.10770 0.10082 -0.0278 1.0000 0.0779
-8.250 -0.3561 0.10668 0.09994 -0.0294 1.0000 0.0788
-8.000 -0.3633 0.10553 0.09894 -0.0310 1.0000 0.0792
-7.750 -0.3431 0.09864 0.09202 -0.0278 1.0000 0.0832
-7.500 -0.3417 0.09604 0.08951 -0.0273 1.0000 0.0861
-7.250 -0.3432 0.09379 0.08737 -0.0273 1.0000 0.0886
-7.000 -0.3451 0.09177 0.08545 -0.0290 1.0000 0.0913
-6.750 -0.3472 0.09032 0.08410 -0.0331 1.0000 0.0930
-6.500 -0.3447 0.08831 0.08212 -0.0370 1.0000 0.0936
-6.250 -0.3407 0.08382 0.07775 -0.0340 1.0000 0.0948
-6.000 -0.3367 0.08041 0.07437 -0.0315 1.0000 0.0968
-5.750 -0.3331 0.07762 0.07163 -0.0309 1.0000 0.0991
-5.500 -0.3289 0.07496 0.06900 -0.0313 1.0000 0.1020
-5.250 -0.3154 0.07334 0.06716 -0.0396 1.0000 0.1082
-4.250 -0.2586 0.05594 0.04925 -0.0440 1.0000 0.0660
-4.000 -0.2404 0.05246 0.04567 -0.0448 0.9978 0.0640
-3.750 -0.2031 0.04808 0.04098 -0.0500 0.9908 0.0677
-3.500 -0.1677 0.04467 0.03729 -0.0539 0.9838 0.0709
-3.250 -0.1269 0.04053 0.03257 -0.0583 0.9773 0.0700
-3.000 -0.0901 0.03770 0.02923 -0.0614 0.9696 0.0758
-2.750 -0.0506 0.03479 0.02557 -0.0643 0.9628 0.0782
-2.500 -0.0130 0.03235 0.02246 -0.0665 0.9553 0.0791
-2.250 0.0226 0.03028 0.02000 -0.0684 0.9470 0.0810
-2.000 0.0621 0.02899 0.01842 -0.0711 0.9387 0.0896
-1.750 0.0992 0.02766 0.01651 -0.0725 0.9280 0.0934
-1.500 0.1365 0.02632 0.01492 -0.0742 0.9183 0.0957
-1.250 0.1783 0.02521 0.01355 -0.0765 0.9105 0.0997
-1.000 0.2142 0.02444 0.01250 -0.0777 0.9001 0.1048
-0.750 0.2520 0.02368 0.01159 -0.0793 0.8914 0.1123
-0.500 0.2899 0.02307 0.01093 -0.0811 0.8829 0.1320
-0.250 0.3218 0.02254 0.01043 -0.0818 0.8721 0.1553
0.000 0.3551 0.02185 0.01000 -0.0828 0.8620 0.2124
0.250 0.4038 0.01949 0.00939 -0.0865 0.8553 1.0000
0.500 0.4340 0.01960 0.00920 -0.0867 0.8432 1.0000
0.750 0.4640 0.01971 0.00908 -0.0868 0.8312 1.0000
1.000 0.4940 0.01982 0.00901 -0.0869 0.8191 1.0000
1.250 0.5241 0.01992 0.00896 -0.0869 0.8071 1.0000
1.500 0.5546 0.02001 0.00894 -0.0870 0.7952 1.0000
1.750 0.5851 0.02008 0.00893 -0.0870 0.7833 1.0000
2.000 0.6127 0.02024 0.00902 -0.0866 0.7696 1.0000
2.250 0.6399 0.02041 0.00917 -0.0862 0.7558 1.0000
2.500 0.6670 0.02059 0.00932 -0.0856 0.7418 1.0000
2.750 0.6938 0.02078 0.00949 -0.0850 0.7273 1.0000
3.000 0.7202 0.02098 0.00970 -0.0844 0.7127 1.0000
3.250 0.7465 0.02119 0.00994 -0.0836 0.6975 1.0000
3.500 0.7724 0.02140 0.01018 -0.0829 0.6822 1.0000
3.750 0.7974 0.02165 0.01047 -0.0820 0.6662 1.0000
4.000 0.8213 0.02196 0.01088 -0.0810 0.6495 1.0000
4.250 0.8455 0.02227 0.01127 -0.0800 0.6333 1.0000
4.500 0.8698 0.02259 0.01169 -0.0791 0.6177 1.0000
4.750 0.8941 0.02294 0.01219 -0.0782 0.6027 1.0000
5.000 0.9185 0.02332 0.01271 -0.0774 0.5883 1.0000
5.250 0.9428 0.02373 0.01326 -0.0765 0.5741 1.0000
5.500 0.9670 0.02416 0.01387 -0.0757 0.5605 1.0000
5.750 0.9905 0.02457 0.01449 -0.0747 0.5452 1.0000
6.000 1.0133 0.02481 0.01487 -0.0732 0.5259 1.0000
6.250 1.0339 0.02506 0.01525 -0.0714 0.5030 1.0000
6.500 1.0538 0.02526 0.01553 -0.0694 0.4770 1.0000
6.750 1.0717 0.02559 0.01593 -0.0672 0.4482 1.0000
7.000 1.0884 0.02604 0.01656 -0.0650 0.4185 1.0000
7.250 1.1018 0.02661 0.01724 -0.0623 0.3818 1.0000
7.500 1.1128 0.02729 0.01806 -0.0595 0.3367 1.0000
7.750 1.1169 0.02843 0.01896 -0.0559 0.2559 1.0000
8.000 1.1110 0.03096 0.02058 -0.0520 0.1507 1.0000
8.250 1.1055 0.03390 0.02290 -0.0489 0.1118 1.0000
8.500 1.1033 0.03639 0.02527 -0.0458 0.0912 1.0000
8.750 1.1016 0.03881 0.02771 -0.0429 0.0786 1.0000
9.000 1.0995 0.04137 0.03024 -0.0403 0.0697 1.0000
9.250 1.1013 0.04375 0.03277 -0.0381 0.0609 1.0000
9.500 1.1050 0.04631 0.03536 -0.0360 0.0554 1.0000
10.000 1.1328 0.05093 0.04025 -0.0327 0.0440 1.0000
10.250 1.1584 0.05332 0.04308 -0.0314 0.0402 1.0000
10.500 1.1769 0.05612 0.04616 -0.0303 0.0373 1.0000
10.750 1.1873 0.05894 0.04909 -0.0293 0.0350 1.0000
11.000 1.1914 0.06233 0.05282 -0.0279 0.0334 1.0000
11.250 1.1902 0.06591 0.05681 -0.0264 0.0324 1.0000
11.500 1.1849 0.06982 0.06110 -0.0254 0.0319 1.0000
11.750 1.1766 0.07396 0.06555 -0.0248 0.0316 1.0000
12.000 1.1646 0.07850 0.07039 -0.0248 0.0315 1.0000
12.250 1.1504 0.08343 0.07558 -0.0256 0.0314 1.0000
12.500 1.1342 0.08885 0.08125 -0.0272 0.0315 1.0000
12.750 1.1162 0.09486 0.08748 -0.0296 0.0316 1.0000
13.000 1.0982 0.10134 0.09415 -0.0328 0.0318 1.0000
13.250 1.0795 0.10847 0.10144 -0.0368 0.0321 1.0000
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Polar data table (+)
Polar graphs
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