GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 367 AIRFOIL (goe367-il) Reynolds number: 200,000 Max Cl/Cd: 64.79 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe367-il-200000-n5.txt Download as CSV file: xf-goe367-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 367 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2401 0.09015 0.08605 -0.0869 0.9440 0.0423
-10.750 -0.4886 0.04289 0.03790 -0.1151 0.9092 0.0423
-10.500 -0.5113 0.03825 0.03274 -0.1123 0.8976 0.0427
-10.250 -0.5157 0.03505 0.02908 -0.1100 0.8889 0.0432
-10.000 -0.5128 0.03254 0.02610 -0.1078 0.8808 0.0439
-9.750 -0.5044 0.03053 0.02362 -0.1059 0.8736 0.0446
-9.500 -0.4850 0.02941 0.02242 -0.1051 0.8685 0.0451
-9.250 -0.4662 0.02850 0.02143 -0.1042 0.8612 0.0456
-9.000 -0.4463 0.02752 0.02032 -0.1033 0.8554 0.0461
-8.750 -0.4255 0.02653 0.01915 -0.1025 0.8505 0.0466
-8.500 -0.4054 0.02559 0.01806 -0.1016 0.8435 0.0473
-8.250 -0.3839 0.02464 0.01691 -0.1008 0.8373 0.0480
-8.000 -0.3614 0.02372 0.01578 -0.1001 0.8316 0.0488
-7.750 -0.3391 0.02292 0.01478 -0.0993 0.8243 0.0497
-7.500 -0.3153 0.02218 0.01383 -0.0987 0.8186 0.0506
-7.250 -0.2909 0.02146 0.01309 -0.0983 0.8137 0.0515
-7.000 -0.2670 0.02092 0.01253 -0.0978 0.8074 0.0524
-6.750 -0.2421 0.02037 0.01190 -0.0974 0.8021 0.0534
-6.500 -0.2164 0.01980 0.01122 -0.0971 0.7977 0.0545
-6.250 -0.1917 0.01929 0.01062 -0.0966 0.7918 0.0556
-6.000 -0.1664 0.01881 0.01003 -0.0962 0.7863 0.0568
-5.750 -0.1409 0.01828 0.00946 -0.0958 0.7815 0.0581
-5.500 -0.1155 0.01789 0.00906 -0.0955 0.7766 0.0597
-5.250 -0.0903 0.01754 0.00869 -0.0951 0.7708 0.0615
-5.000 -0.0644 0.01717 0.00825 -0.0947 0.7655 0.0634
-4.750 -0.0380 0.01679 0.00779 -0.0944 0.7612 0.0652
-4.500 -0.0133 0.01648 0.00752 -0.0940 0.7551 0.0673
-4.250 0.0125 0.01621 0.00723 -0.0936 0.7494 0.0700
-4.000 0.0391 0.01594 0.00690 -0.0933 0.7444 0.0733
-3.750 0.0648 0.01571 0.00671 -0.0930 0.7387 0.0770
-3.250 0.1172 0.01531 0.00629 -0.0923 0.7270 0.0873
-3.000 0.1434 0.01514 0.00614 -0.0920 0.7210 0.0948
-2.750 0.1693 0.01501 0.00599 -0.0916 0.7139 0.1038
-2.500 0.1963 0.01486 0.00582 -0.0914 0.7077 0.1131
-2.250 0.2216 0.01474 0.00572 -0.0910 0.6996 0.1220
-2.000 0.2482 0.01465 0.00556 -0.0906 0.6917 0.1308
-1.750 0.2737 0.01450 0.00544 -0.0902 0.6838 0.1388
-1.500 0.2998 0.01442 0.00531 -0.0899 0.6756 0.1468
-1.250 0.3256 0.01427 0.00518 -0.0895 0.6685 0.1552
-1.000 0.3511 0.01420 0.00509 -0.0890 0.6600 0.1635
-0.750 0.3769 0.01405 0.00496 -0.0887 0.6529 0.1749
-0.500 0.4017 0.01394 0.00491 -0.0882 0.6442 0.1892
-0.250 0.4268 0.01377 0.00481 -0.0877 0.6364 0.2148
0.000 0.4495 0.01343 0.00477 -0.0869 0.6273 0.2895
0.250 0.4664 0.01261 0.00472 -0.0851 0.6190 0.5225
0.500 0.4877 0.01206 0.00529 -0.0824 0.6099 0.8634
0.750 0.5150 0.01227 0.00542 -0.0817 0.6011 0.9092
1.000 0.5423 0.01248 0.00558 -0.0811 0.5915 0.9374
1.250 0.5835 0.01272 0.00571 -0.0836 0.5822 0.9550
1.500 0.6263 0.01293 0.00583 -0.0866 0.5719 0.9673
1.750 0.6792 0.01312 0.00590 -0.0920 0.5614 0.9749
2.000 0.7230 0.01330 0.00595 -0.0954 0.5509 0.9830
2.250 0.7703 0.01345 0.00602 -0.0998 0.5405 0.9906
2.500 0.8128 0.01361 0.00606 -0.1031 0.5312 0.9960
2.750 0.8501 0.01375 0.00615 -0.1054 0.5220 1.0000
3.000 0.8699 0.01392 0.00624 -0.1040 0.5144 1.0000
3.250 0.8896 0.01407 0.00637 -0.1026 0.5063 1.0000
3.500 0.9079 0.01427 0.00649 -0.1010 0.4978 1.0000
3.750 0.9259 0.01445 0.00664 -0.0992 0.4890 1.0000
4.000 0.9426 0.01467 0.00679 -0.0972 0.4801 1.0000
4.250 0.9592 0.01485 0.00695 -0.0952 0.4715 1.0000
4.500 0.9743 0.01508 0.00712 -0.0929 0.4631 1.0000
4.750 0.9894 0.01528 0.00730 -0.0907 0.4554 1.0000
5.000 1.0036 0.01549 0.00749 -0.0882 0.4481 1.0000
5.250 1.0169 0.01571 0.00767 -0.0856 0.4415 1.0000
5.500 1.0302 0.01591 0.00788 -0.0829 0.4347 1.0000
5.750 1.0420 0.01614 0.00808 -0.0800 0.4285 1.0000
6.000 1.0546 0.01636 0.00829 -0.0773 0.4228 1.0000
6.250 1.0661 0.01658 0.00851 -0.0743 0.4168 1.0000
6.500 1.0759 0.01684 0.00873 -0.0711 0.4108 1.0000
6.750 1.0886 0.01710 0.00900 -0.0685 0.4046 1.0000
7.000 1.1025 0.01740 0.00931 -0.0662 0.3979 1.0000
7.250 1.1174 0.01776 0.00963 -0.0642 0.3925 1.0000
7.500 1.1350 0.01809 0.01000 -0.0627 0.3873 1.0000
7.750 1.1523 0.01845 0.01038 -0.0613 0.3821 1.0000
8.000 1.1689 0.01887 0.01079 -0.0597 0.3770 1.0000
8.250 1.1864 0.01928 0.01122 -0.0584 0.3719 1.0000
8.500 1.2039 0.01971 0.01170 -0.0571 0.3665 1.0000
8.750 1.2210 0.02018 0.01218 -0.0558 0.3618 1.0000
9.000 1.2381 0.02068 0.01268 -0.0546 0.3578 1.0000
9.250 1.2565 0.02113 0.01322 -0.0536 0.3536 1.0000
9.500 1.2741 0.02164 0.01379 -0.0525 0.3492 1.0000
9.750 1.2904 0.02220 0.01439 -0.0513 0.3446 1.0000
10.000 1.3061 0.02281 0.01500 -0.0500 0.3402 1.0000
10.250 1.3223 0.02341 0.01571 -0.0489 0.3349 1.0000
10.500 1.3366 0.02410 0.01645 -0.0476 0.3290 1.0000
10.750 1.3497 0.02488 0.01723 -0.0461 0.3236 1.0000
11.000 1.3643 0.02561 0.01808 -0.0450 0.3176 1.0000
11.250 1.3765 0.02648 0.01900 -0.0436 0.3109 1.0000
11.500 1.3875 0.02744 0.02001 -0.0422 0.3040 1.0000
11.750 1.3970 0.02853 0.02116 -0.0408 0.2945 1.0000
12.000 1.4044 0.02978 0.02245 -0.0393 0.2831 1.0000
12.250 1.4095 0.03123 0.02394 -0.0376 0.2692 1.0000
12.500 1.4125 0.03291 0.02562 -0.0360 0.2511 1.0000
12.750 1.4073 0.03527 0.02789 -0.0340 0.2219 1.0000
13.000 1.3905 0.03876 0.03118 -0.0315 0.1894 1.0000
13.250 1.3776 0.04216 0.03448 -0.0297 0.1723 1.0000
13.500 1.3685 0.04543 0.03772 -0.0282 0.1608 1.0000
13.750 1.3651 0.04828 0.04060 -0.0272 0.1511 1.0000
14.000 1.3608 0.05130 0.04367 -0.0263 0.1423 1.0000
14.250 1.3563 0.05446 0.04687 -0.0256 0.1316 1.0000
14.500 1.3523 0.05767 0.05012 -0.0251 0.1181 1.0000
14.750 1.3435 0.06150 0.05394 -0.0247 0.1055 1.0000
15.000 1.3340 0.06552 0.05794 -0.0245 0.0976 1.0000
15.250 1.3262 0.06944 0.06188 -0.0244 0.0934 1.0000
15.500 1.3184 0.07343 0.06591 -0.0244 0.0899 1.0000
15.750 1.3118 0.07733 0.06985 -0.0245 0.0870 1.0000
16.000 1.3074 0.08100 0.07360 -0.0247 0.0845 1.0000
16.250 1.3018 0.08484 0.07751 -0.0250 0.0820 1.0000
16.500 1.2949 0.08888 0.08159 -0.0254 0.0799 1.0000
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