GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 100,000 Max Cl/Cd: 61.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe381-il-100000-n5.txt Download as CSV file: xf-goe381-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2675 0.09832 0.09409 -0.0224 1.0000 0.0282
-7.000 -0.2757 0.09731 0.09318 -0.0205 1.0000 0.0285
-6.750 -0.2789 0.09595 0.09189 -0.0202 0.9992 0.0288
-6.500 -0.2503 0.09245 0.08838 -0.0290 0.9909 0.0293
-6.250 -0.2193 0.08879 0.08465 -0.0379 0.9830 0.0295
-6.000 -0.1857 0.08486 0.08066 -0.0468 0.9763 0.0297
-5.750 -0.1531 0.08089 0.07663 -0.0544 0.9688 0.0298
-5.500 -0.1191 0.07675 0.07240 -0.0615 0.9624 0.0298
-5.250 -0.0827 0.07274 0.06828 -0.0685 0.9557 0.0300
-5.000 -0.0796 0.06652 0.06221 -0.0655 0.9509 0.0315
-4.750 -0.0542 0.06292 0.05857 -0.0689 0.9428 0.0334
-4.500 -0.0208 0.05927 0.05482 -0.0744 0.9356 0.0352
-4.250 0.0162 0.05581 0.05122 -0.0802 0.9275 0.0379
-4.000 0.0726 0.05370 0.04872 -0.0893 0.9185 0.0403
-3.750 0.0957 0.04870 0.04374 -0.0916 0.9118 0.0416
-3.500 0.1340 0.04757 0.04233 -0.0950 0.9016 0.0521
-3.250 0.1579 0.04306 0.03780 -0.0968 0.8935 0.0541
-3.000 0.1837 0.04021 0.03486 -0.0981 0.8843 0.0583
-2.500 0.2479 0.03535 0.02957 -0.1017 0.8644 0.0720
-2.250 0.2896 0.03193 0.02561 -0.1038 0.8554 0.0543
-2.000 0.3200 0.02955 0.02294 -0.1043 0.8439 0.0499
-1.750 0.3540 0.02784 0.02072 -0.1046 0.8327 0.0521
-1.500 0.3832 0.02569 0.01827 -0.1049 0.8213 0.0514
-1.250 0.4134 0.02400 0.01621 -0.1049 0.8093 0.0532
-1.000 0.4393 0.02303 0.01517 -0.1049 0.7949 0.0579
-0.750 0.4687 0.02160 0.01336 -0.1045 0.7794 0.0560
-0.500 0.4975 0.02033 0.01167 -0.1039 0.7624 0.0545
-0.250 0.5252 0.01929 0.01031 -0.1032 0.7438 0.0539
0.000 0.5523 0.01840 0.00914 -0.1025 0.7240 0.0540
0.250 0.5787 0.01769 0.00821 -0.1018 0.7018 0.0548
0.500 0.6051 0.01713 0.00746 -0.1010 0.6820 0.0563
0.750 0.6316 0.01669 0.00687 -0.1005 0.6646 0.0587
1.000 0.6576 0.01637 0.00640 -0.0998 0.6494 0.0632
1.250 0.6835 0.01627 0.00623 -0.0993 0.6345 0.0711
1.500 0.7098 0.01609 0.00590 -0.0987 0.6204 0.0763
1.750 0.7363 0.01596 0.00561 -0.0983 0.6066 0.0819
2.000 0.7628 0.01592 0.00543 -0.0979 0.5925 0.0946
2.250 0.7892 0.01593 0.00533 -0.0975 0.5784 0.1193
2.500 0.8153 0.01598 0.00530 -0.0971 0.5639 0.1495
3.000 0.8648 0.01485 0.00548 -0.0960 0.5340 1.0000
3.250 0.8901 0.01511 0.00561 -0.0955 0.5184 1.0000
3.500 0.9154 0.01539 0.00578 -0.0950 0.5026 1.0000
3.750 0.9405 0.01566 0.00601 -0.0945 0.4864 1.0000
4.000 0.9654 0.01594 0.00623 -0.0940 0.4692 1.0000
4.250 0.9900 0.01623 0.00647 -0.0935 0.4504 1.0000
4.500 1.0143 0.01655 0.00677 -0.0929 0.4303 1.0000
4.750 1.0384 0.01688 0.00706 -0.0923 0.4080 1.0000
5.000 1.0618 0.01727 0.00737 -0.0917 0.3850 1.0000
5.250 1.0847 0.01772 0.00773 -0.0910 0.3621 1.0000
5.500 1.1074 0.01821 0.00819 -0.0903 0.3422 1.0000
5.750 1.1300 0.01873 0.00867 -0.0896 0.3253 1.0000
6.000 1.1525 0.01927 0.00921 -0.0889 0.3105 1.0000
6.250 1.1722 0.01999 0.00978 -0.0879 0.2823 1.0000
6.500 1.1908 0.02082 0.01041 -0.0868 0.2499 1.0000
6.750 1.2107 0.02155 0.01111 -0.0859 0.2275 1.0000
7.000 1.2302 0.02232 0.01182 -0.0849 0.1999 1.0000
7.250 1.2505 0.02303 0.01254 -0.0840 0.1687 1.0000
7.500 1.2601 0.02486 0.01376 -0.0821 0.1094 1.0000
7.750 1.2687 0.02688 0.01542 -0.0799 0.0297 1.0000
8.000 1.2813 0.02841 0.01700 -0.0779 0.0232 1.0000
8.250 1.2956 0.02967 0.01853 -0.0761 0.0205 1.0000
8.500 1.3085 0.03102 0.02013 -0.0742 0.0190 1.0000
8.750 1.3194 0.03249 0.02186 -0.0722 0.0181 1.0000
9.000 1.3264 0.03408 0.02371 -0.0697 0.0174 1.0000
9.250 1.3297 0.03590 0.02579 -0.0670 0.0167 1.0000
9.500 1.3290 0.03807 0.02820 -0.0644 0.0160 1.0000
9.750 1.3239 0.04066 0.03105 -0.0619 0.0152 1.0000
10.000 1.3153 0.04372 0.03436 -0.0598 0.0147 1.0000
10.250 1.3051 0.04717 0.03802 -0.0583 0.0143 1.0000
10.500 1.2946 0.05093 0.04198 -0.0573 0.0140 1.0000
10.750 1.2886 0.05444 0.04562 -0.0568 0.0139 1.0000
11.000 1.2836 0.05800 0.04933 -0.0565 0.0138 1.0000
11.250 1.2797 0.06151 0.05297 -0.0562 0.0137 1.0000
11.500 1.2778 0.06478 0.05635 -0.0558 0.0136 1.0000
11.750 1.2791 0.06760 0.05933 -0.0549 0.0135 1.0000
12.000 1.2844 0.06989 0.06168 -0.0534 0.0134 1.0000
12.250 1.2941 0.07176 0.06359 -0.0515 0.0133 1.0000
12.500 1.3058 0.07366 0.06558 -0.0496 0.0131 1.0000
12.750 1.3128 0.07625 0.06833 -0.0485 0.0129 1.0000
13.000 1.3152 0.07943 0.07170 -0.0482 0.0125 1.0000
13.250 1.3157 0.08289 0.07536 -0.0481 0.0121 1.0000
13.500 1.3144 0.08665 0.07932 -0.0483 0.0118 1.0000
13.750 1.3109 0.09076 0.08364 -0.0489 0.0116 1.0000
14.000 1.3060 0.09516 0.08826 -0.0497 0.0115 1.0000
14.250 1.2998 0.09991 0.09323 -0.0510 0.0114 1.0000
14.500 1.2922 0.10500 0.09853 -0.0527 0.0115 1.0000
14.750 1.2834 0.11044 0.10419 -0.0549 0.0115 1.0000
15.000 1.2736 0.11622 0.11018 -0.0575 0.0116 1.0000
15.250 1.2631 0.12234 0.11651 -0.0607 0.0117 1.0000
15.500 1.2521 0.12883 0.12320 -0.0643 0.0118 1.0000
15.750 1.2408 0.13572 0.13028 -0.0685 0.0118 1.0000
16.000 1.2296 0.14294 0.13768 -0.0732 0.0119 1.0000
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Polar data table (+)
Polar graphs
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