GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 407 AIRFOIL (goe407-il) Reynolds number: 200,000 Max Cl/Cd: 79.38 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe407-il-200000.txt Download as CSV file: xf-goe407-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 407 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2500 0.09608 0.09288 -0.0297 1.0000 0.0434
-8.500 -0.2649 0.09467 0.09154 -0.0298 1.0000 0.0438
-8.250 -0.2845 0.09377 0.09074 -0.0288 1.0000 0.0440
-8.000 -0.2916 0.09106 0.08807 -0.0329 0.9966 0.0441
-7.750 -0.2689 0.08468 0.08169 -0.0334 0.9946 0.0447
-7.500 -0.2449 0.08007 0.07707 -0.0343 0.9915 0.0457
-7.250 -0.2277 0.07576 0.07275 -0.0380 0.9866 0.0469
-7.000 -0.3376 0.08551 0.08234 -0.0352 0.9904 0.0448
-6.750 -0.3141 0.08168 0.07850 -0.0369 0.9862 0.0457
-6.500 -0.2873 0.07768 0.07447 -0.0419 0.9802 0.0471
-6.250 -0.2580 0.07348 0.07021 -0.0488 0.9730 0.0497
-6.000 -0.2152 0.06760 0.06399 -0.0655 0.9599 0.0530
-5.750 -0.1927 0.06323 0.05969 -0.0666 0.9571 0.0538
-5.500 -0.1734 0.06023 0.05671 -0.0674 0.9472 0.0549
-5.250 -0.1409 0.05675 0.05315 -0.0717 0.9430 0.0571
-5.000 -0.0994 0.05443 0.05027 -0.0787 0.9300 0.0627
-4.750 -0.0816 0.04929 0.04515 -0.0799 0.9211 0.0637
-4.500 -0.0560 0.04614 0.04208 -0.0814 0.9158 0.0653
-4.250 0.0263 0.02713 0.02269 -0.0885 0.8889 0.0748
-4.000 0.0492 0.02252 0.01821 -0.0904 0.8843 0.0763
-3.750 0.0346 0.03773 0.03304 -0.0872 0.8916 0.0763
-3.500 0.0664 0.03519 0.03048 -0.0893 0.8854 0.0786
-3.250 0.1040 0.03561 0.03026 -0.0900 0.8750 0.0877
-3.000 0.1340 0.03056 0.02529 -0.0927 0.8679 0.0903
-2.750 0.1635 0.02872 0.02337 -0.0936 0.8550 0.0939
-2.500 0.1925 0.02721 0.02150 -0.0938 0.8419 0.1048
-2.250 0.2204 0.02576 0.01998 -0.0942 0.8303 0.1102
-2.000 0.2485 0.02446 0.01838 -0.0943 0.8200 0.1212
-1.750 0.2713 0.02380 0.01748 -0.0931 0.8085 0.1348
-1.500 0.2945 0.02246 0.01612 -0.0925 0.7983 0.1407
-1.250 0.3289 0.01909 0.01168 -0.0901 0.7903 0.0771
-1.000 0.3545 0.01780 0.01017 -0.0889 0.7807 0.0688
-0.750 0.3838 0.01695 0.00907 -0.0887 0.7726 0.0683
-0.500 0.4081 0.01620 0.00816 -0.0875 0.7628 0.0672
-0.250 0.4374 0.01550 0.00724 -0.0873 0.7548 0.0658
0.000 0.4622 0.01498 0.00668 -0.0863 0.7450 0.0659
0.250 0.4890 0.01453 0.00619 -0.0858 0.7367 0.0670
0.500 0.5138 0.01416 0.00581 -0.0849 0.7274 0.0685
0.750 0.5382 0.01388 0.00551 -0.0839 0.7185 0.0713
1.000 0.5629 0.01362 0.00522 -0.0829 0.7096 0.0759
1.250 0.5848 0.01335 0.00500 -0.0815 0.7000 0.0825
1.500 0.7549 0.01104 0.00468 -0.1129 0.6850 1.0000
1.750 0.7795 0.01115 0.00464 -0.1120 0.6753 1.0000
2.000 0.8016 0.01127 0.00470 -0.1107 0.6637 1.0000
2.250 0.8245 0.01140 0.00475 -0.1095 0.6522 1.0000
2.500 0.8477 0.01154 0.00478 -0.1083 0.6405 1.0000
2.750 0.8705 0.01168 0.00483 -0.1071 0.6279 1.0000
3.000 0.8918 0.01181 0.00494 -0.1055 0.6138 1.0000
3.250 0.9129 0.01195 0.00502 -0.1040 0.5986 1.0000
3.500 0.9337 0.01209 0.00510 -0.1023 0.5822 1.0000
3.750 0.9541 0.01224 0.00518 -0.1006 0.5649 1.0000
4.000 0.9741 0.01239 0.00528 -0.0988 0.5467 1.0000
4.250 0.9934 0.01255 0.00540 -0.0969 0.5260 1.0000
4.500 1.0121 0.01275 0.00551 -0.0949 0.5044 1.0000
4.750 1.0306 0.01302 0.00564 -0.0930 0.4842 1.0000
5.000 1.0495 0.01332 0.00586 -0.0911 0.4653 1.0000
5.250 1.0688 0.01367 0.00611 -0.0894 0.4492 1.0000
5.500 1.0884 0.01406 0.00640 -0.0877 0.4352 1.0000
5.750 1.1081 0.01446 0.00673 -0.0861 0.4221 1.0000
6.000 1.1279 0.01482 0.00707 -0.0846 0.4095 1.0000
6.250 1.1476 0.01519 0.00743 -0.0830 0.3980 1.0000
6.500 1.1679 0.01562 0.00779 -0.0816 0.3884 1.0000
6.750 1.1872 0.01596 0.00818 -0.0800 0.3780 1.0000
7.000 1.2066 0.01634 0.00857 -0.0785 0.3685 1.0000
7.250 1.2254 0.01675 0.00893 -0.0768 0.3589 1.0000
7.500 1.2438 0.01706 0.00934 -0.0750 0.3496 1.0000
7.750 1.2621 0.01748 0.00974 -0.0733 0.3408 1.0000
8.000 1.2790 0.01779 0.01015 -0.0713 0.3314 1.0000
8.250 1.2958 0.01817 0.01056 -0.0693 0.3223 1.0000
8.500 1.3109 0.01855 0.01096 -0.0669 0.3122 1.0000
8.750 1.3243 0.01887 0.01139 -0.0643 0.3004 1.0000
9.000 1.3357 0.01924 0.01181 -0.0613 0.2871 1.0000
9.250 1.3441 0.01962 0.01222 -0.0577 0.2726 1.0000
9.500 1.3502 0.02002 0.01264 -0.0538 0.2575 1.0000
9.750 1.3552 0.02051 0.01313 -0.0498 0.2395 1.0000
10.000 1.3585 0.02117 0.01373 -0.0457 0.2196 1.0000
10.250 1.3631 0.02193 0.01447 -0.0421 0.1952 1.0000
10.500 1.3658 0.02289 0.01534 -0.0384 0.1731 1.0000
10.750 1.3684 0.02397 0.01633 -0.0349 0.1559 1.0000
11.000 1.3707 0.02516 0.01746 -0.0316 0.1443 1.0000
11.250 1.3713 0.02651 0.01875 -0.0284 0.1353 1.0000
11.500 1.3753 0.02777 0.02006 -0.0258 0.1273 1.0000
11.750 1.3760 0.02930 0.02160 -0.0230 0.1210 1.0000
12.000 1.3812 0.03063 0.02304 -0.0209 0.1144 1.0000
12.250 1.3794 0.03254 0.02491 -0.0185 0.1086 1.0000
12.500 1.3870 0.03383 0.02639 -0.0170 0.1016 1.0000
12.750 1.3863 0.03583 0.02842 -0.0152 0.0937 1.0000
13.000 1.3878 0.03778 0.03044 -0.0138 0.0828 1.0000
13.250 1.3902 0.03980 0.03250 -0.0127 0.0657 1.0000
13.500 1.3824 0.04286 0.03551 -0.0114 0.0540 1.0000
13.750 1.3741 0.04611 0.03878 -0.0102 0.0480 1.0000
14.000 1.3657 0.04950 0.04220 -0.0095 0.0440 1.0000
14.250 1.3575 0.05302 0.04578 -0.0089 0.0413 1.0000
14.500 1.3525 0.05625 0.04913 -0.0084 0.0395 1.0000
14.750 1.3452 0.05988 0.05282 -0.0083 0.0373 1.0000
15.000 1.3365 0.06373 0.05674 -0.0083 0.0362 1.0000
15.250 1.3285 0.06762 0.06071 -0.0084 0.0348 1.0000
15.500 1.3244 0.07113 0.06435 -0.0085 0.0336 1.0000
15.750 1.3202 0.07472 0.06804 -0.0088 0.0327 1.0000
16.000 1.3160 0.07832 0.07174 -0.0091 0.0319 1.0000
16.250 1.3111 0.08206 0.07555 -0.0096 0.0310 1.0000
16.500 1.3073 0.08562 0.07914 -0.0099 0.0302 1.0000
16.750 1.3067 0.08833 0.08183 -0.0093 0.0294 1.0000
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