GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 50,000 Max Cl/Cd: 42.98 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe381-il-50000-n5.txt Download as CSV file: xf-goe381-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2724 0.10804 0.10188 -0.0259 1.0000 0.0514
-7.500 -0.2763 0.10752 0.10150 -0.0266 1.0000 0.0519
-7.250 -0.2784 0.10694 0.10103 -0.0280 1.0000 0.0521
-7.000 -0.2790 0.10625 0.10043 -0.0297 1.0000 0.0523
-6.750 -0.2774 0.10205 0.09634 -0.0278 1.0000 0.0529
-6.500 -0.2753 0.09690 0.09126 -0.0237 1.0000 0.0544
-6.250 -0.2755 0.09435 0.08878 -0.0223 1.0000 0.0557
-6.000 -0.2756 0.09218 0.08667 -0.0216 1.0000 0.0571
-5.750 -0.2748 0.09010 0.08463 -0.0213 1.0000 0.0587
-5.500 -0.2724 0.08805 0.08263 -0.0216 1.0000 0.0605
-5.250 -0.2673 0.08613 0.08075 -0.0229 1.0000 0.0627
-5.000 -0.2357 0.08489 0.07941 -0.0325 0.9960 0.0654
-4.750 -0.2013 0.08004 0.07451 -0.0396 0.9881 0.0666
-4.500 -0.1850 0.07463 0.06914 -0.0398 0.9812 0.0704
-4.250 -0.1216 0.07299 0.06713 -0.0547 0.9708 0.0799
-4.000 -0.1055 0.06675 0.06102 -0.0549 0.9643 0.0832
-3.750 -0.0692 0.06300 0.05712 -0.0604 0.9554 0.0899
-3.250 0.0150 0.05541 0.04920 -0.0732 0.9390 0.1012
-3.000 0.0546 0.05218 0.04576 -0.0784 0.9289 0.1119
-2.750 0.0990 0.04908 0.04239 -0.0842 0.9202 0.1235
-2.250 0.1780 0.04286 0.03572 -0.0924 0.9022 0.1538
-2.000 0.2106 0.03984 0.03260 -0.0954 0.8935 0.2098
-1.500 0.3157 0.03551 0.02681 -0.1017 0.8741 0.0819
-1.250 0.3509 0.03373 0.02477 -0.1034 0.8641 0.0880
-1.000 0.3908 0.03198 0.02253 -0.1051 0.8549 0.0832
-0.500 0.4570 0.02972 0.01940 -0.1059 0.8310 0.0797
-0.250 0.4886 0.02866 0.01803 -0.1062 0.8193 0.0796
0.000 0.5204 0.02772 0.01681 -0.1063 0.8081 0.0802
0.250 0.5523 0.02672 0.01563 -0.1065 0.7975 0.0829
0.500 0.5814 0.02628 0.01493 -0.1062 0.7842 0.0925
0.750 0.6106 0.02555 0.01402 -0.1056 0.7698 0.0981
1.000 0.6391 0.02480 0.01307 -0.1047 0.7542 0.1019
1.250 0.6654 0.02423 0.01228 -0.1034 0.7365 0.1066
1.500 0.6911 0.02366 0.01161 -0.1022 0.7185 0.1135
1.750 0.7176 0.02318 0.01099 -0.1013 0.7017 0.1256
2.000 0.7446 0.02274 0.01045 -0.1007 0.6862 0.1513
2.250 0.7688 0.02087 0.01018 -0.0998 0.6720 1.0000
2.500 0.7951 0.02104 0.01003 -0.0989 0.6574 1.0000
2.750 0.8211 0.02124 0.00999 -0.0981 0.6426 1.0000
3.000 0.8468 0.02146 0.01005 -0.0974 0.6276 1.0000
3.250 0.8723 0.02172 0.01016 -0.0966 0.6125 1.0000
3.500 0.8976 0.02199 0.01031 -0.0958 0.5971 1.0000
3.750 0.9227 0.02229 0.01054 -0.0951 0.5814 1.0000
4.000 0.9476 0.02262 0.01079 -0.0943 0.5655 1.0000
4.250 0.9722 0.02299 0.01111 -0.0935 0.5492 1.0000
4.500 0.9958 0.02343 0.01154 -0.0927 0.5316 1.0000
4.750 1.0191 0.02387 0.01203 -0.0918 0.5131 1.0000
5.000 1.0423 0.02432 0.01247 -0.0909 0.4943 1.0000
5.250 1.0651 0.02478 0.01293 -0.0899 0.4753 1.0000
5.500 1.0865 0.02532 0.01353 -0.0889 0.4543 1.0000
5.750 1.1080 0.02581 0.01409 -0.0878 0.4343 1.0000
6.000 1.1287 0.02635 0.01467 -0.0866 0.4136 1.0000
6.250 1.1491 0.02692 0.01528 -0.0855 0.3937 1.0000
6.500 1.1696 0.02751 0.01589 -0.0843 0.3761 1.0000
6.750 1.1902 0.02818 0.01666 -0.0833 0.3607 1.0000
7.000 1.2107 0.02891 0.01748 -0.0822 0.3463 1.0000
7.250 1.2243 0.02966 0.01820 -0.0803 0.3198 1.0000
7.500 1.2366 0.03056 0.01905 -0.0784 0.2935 1.0000
7.750 1.2499 0.03155 0.02002 -0.0767 0.2729 1.0000
8.000 1.2646 0.03256 0.02119 -0.0752 0.2564 1.0000
8.250 1.2752 0.03371 0.02251 -0.0733 0.2336 1.0000
8.500 1.2852 0.03493 0.02384 -0.0714 0.2109 1.0000
8.750 1.2948 0.03620 0.02526 -0.0696 0.1836 1.0000
9.000 1.2945 0.03813 0.02689 -0.0671 0.1316 1.0000
9.250 1.2872 0.04113 0.02941 -0.0646 0.0572 1.0000
9.500 1.2798 0.04448 0.03256 -0.0625 0.0421 1.0000
10.000 1.2756 0.05050 0.03896 -0.0596 0.0352 1.0000
10.250 1.2721 0.05385 0.04255 -0.0587 0.0333 1.0000
10.500 1.2658 0.05769 0.04664 -0.0583 0.0318 1.0000
10.750 1.2570 0.06207 0.05125 -0.0585 0.0308 1.0000
11.000 1.2478 0.06675 0.05615 -0.0591 0.0300 1.0000
11.250 1.2392 0.07157 0.06122 -0.0601 0.0293 1.0000
11.500 1.2294 0.07676 0.06665 -0.0614 0.0287 1.0000
11.750 1.2189 0.08220 0.07232 -0.0629 0.0283 1.0000
12.000 1.2082 0.08780 0.07813 -0.0646 0.0279 1.0000
12.250 1.1976 0.09344 0.08396 -0.0664 0.0276 1.0000
12.500 1.1878 0.09901 0.08971 -0.0681 0.0272 1.0000
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Polar data table (+)
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