GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 50,000 Max Cl/Cd: 27.93 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe612-il-50000-n5.txt Download as CSV file: xf-goe612-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 612 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2936 0.12736 0.12031 -0.0385 1.0000 0.1048
-10.000 -0.3269 0.12033 0.11339 -0.0392 0.9993 0.0902
-9.750 -0.3073 0.11636 0.10940 -0.0423 0.9939 0.0891
-9.500 -0.2944 0.11218 0.10520 -0.0460 0.9877 0.0883
-9.250 -0.2840 0.10773 0.10074 -0.0506 0.9818 0.0882
-9.000 -0.2772 0.10342 0.09642 -0.0546 0.9743 0.0883
-8.750 -0.2694 0.09889 0.09188 -0.0591 0.9677 0.0883
-8.500 -0.2652 0.09454 0.08754 -0.0629 0.9594 0.0881
-8.250 -0.2627 0.09015 0.08314 -0.0667 0.9511 0.0876
-8.000 -0.2631 0.08529 0.07828 -0.0712 0.9426 0.0871
-7.750 -0.2736 0.08075 0.07376 -0.0742 0.9309 0.0865
-7.500 -0.2838 0.07426 0.06721 -0.0797 0.9199 0.0859
-7.250 -0.2965 0.06574 0.05846 -0.0869 0.9100 0.0857
-7.000 -0.3114 0.06055 0.05301 -0.0883 0.8982 0.0861
-6.750 -0.3081 0.05504 0.04704 -0.0916 0.8912 0.0875
-6.500 -0.3108 0.05137 0.04293 -0.0910 0.8813 0.0888
-6.250 -0.2948 0.04717 0.03800 -0.0929 0.8762 0.0905
-6.000 -0.2860 0.04583 0.03656 -0.0910 0.8679 0.0916
-5.750 -0.2644 0.04421 0.03477 -0.0911 0.8623 0.0933
-5.500 -0.2361 0.04246 0.03275 -0.0923 0.8585 0.0959
-5.250 -0.2278 0.04139 0.03143 -0.0899 0.8501 0.0986
-5.000 -0.2045 0.03977 0.02931 -0.0899 0.8450 0.1026
-4.500 -0.1627 0.03818 0.02760 -0.0886 0.8338 0.1097
-4.250 -0.1385 0.03721 0.02627 -0.0883 0.8286 0.1155
-4.000 -0.1086 0.03646 0.02558 -0.0889 0.8250 0.1221
-3.750 -0.0922 0.03599 0.02492 -0.0873 0.8185 0.1291
-3.500 -0.0717 0.03555 0.02451 -0.0864 0.8126 0.1371
-3.250 -0.0418 0.03493 0.02382 -0.0868 0.8087 0.1501
-3.000 -0.0144 0.03452 0.02340 -0.0869 0.8044 0.1656
-2.750 -0.0012 0.03451 0.02337 -0.0850 0.7968 0.1801
-2.500 0.0274 0.03424 0.02317 -0.0852 0.7925 0.2021
-2.250 0.0620 0.03394 0.02288 -0.0863 0.7893 0.2319
-2.000 0.0698 0.03435 0.02335 -0.0836 0.7808 0.2522
-1.750 0.0970 0.03434 0.02338 -0.0835 0.7758 0.2860
-1.250 0.1412 0.03463 0.02375 -0.0819 0.7640 0.3447
-1.000 0.1690 0.03463 0.02373 -0.0818 0.7586 0.3775
-0.750 0.2048 0.03438 0.02351 -0.0828 0.7550 0.4119
-0.500 0.2155 0.03487 0.02401 -0.0804 0.7451 0.4358
-0.250 0.2515 0.03443 0.02360 -0.0810 0.7393 0.4729
0.000 0.2725 0.03438 0.02362 -0.0797 0.7295 0.5070
0.250 0.3062 0.03372 0.02315 -0.0798 0.7223 0.5548
0.750 0.3642 0.03250 0.02286 -0.0785 0.7063 0.7420
1.000 0.4410 0.03167 0.02195 -0.0864 0.7023 1.0000
1.250 0.4500 0.03239 0.02250 -0.0838 0.6908 1.0000
1.500 0.4875 0.03212 0.02199 -0.0847 0.6852 1.0000
1.750 0.5004 0.03270 0.02243 -0.0825 0.6743 1.0000
2.000 0.5345 0.03248 0.02205 -0.0828 0.6676 1.0000
2.250 0.5497 0.03298 0.02243 -0.0809 0.6570 1.0000
2.500 0.5823 0.03275 0.02208 -0.0809 0.6496 1.0000
2.750 0.5966 0.03325 0.02249 -0.0789 0.6382 1.0000
3.000 0.6315 0.03289 0.02202 -0.0791 0.6311 1.0000
3.250 0.6427 0.03350 0.02256 -0.0766 0.6184 1.0000
3.500 0.6826 0.03286 0.02182 -0.0774 0.6121 1.0000
3.750 0.6910 0.03356 0.02248 -0.0746 0.5982 1.0000
4.250 0.7422 0.03342 0.02223 -0.0728 0.5780 1.0000
4.500 0.7539 0.03400 0.02277 -0.0705 0.5640 1.0000
4.750 0.7745 0.03417 0.02290 -0.0691 0.5522 1.0000
5.000 0.8058 0.03379 0.02245 -0.0687 0.5428 1.0000
5.250 0.8178 0.03443 0.02307 -0.0665 0.5285 1.0000
5.500 0.8351 0.03483 0.02343 -0.0649 0.5157 1.0000
5.750 0.8718 0.03415 0.02267 -0.0650 0.5074 1.0000
6.000 0.8833 0.03493 0.02343 -0.0630 0.4934 1.0000
6.250 0.8998 0.03548 0.02394 -0.0614 0.4809 1.0000
6.500 0.9296 0.03525 0.02363 -0.0610 0.4712 1.0000
6.750 0.9483 0.03573 0.02407 -0.0597 0.4596 1.0000
7.000 0.9651 0.03638 0.02468 -0.0583 0.4483 1.0000
7.250 0.9984 0.03603 0.02421 -0.0581 0.4394 1.0000
7.500 1.0081 0.03715 0.02536 -0.0563 0.4279 1.0000
7.750 1.0294 0.03760 0.02575 -0.0553 0.4182 1.0000
8.000 1.0515 0.03801 0.02610 -0.0544 0.4085 1.0000
8.250 1.0645 0.03905 0.02715 -0.0529 0.3987 1.0000
8.500 1.0928 0.03913 0.02713 -0.0525 0.3899 1.0000
8.750 1.0985 0.04062 0.02868 -0.0505 0.3802 1.0000
9.000 1.1306 0.04054 0.02849 -0.0504 0.3720 1.0000
9.250 1.1303 0.04243 0.03050 -0.0482 0.3628 1.0000
9.500 1.1624 0.04238 0.03032 -0.0481 0.3547 1.0000
9.750 1.1592 0.04452 0.03262 -0.0458 0.3462 1.0000
10.000 1.1860 0.04479 0.03284 -0.0453 0.3384 1.0000
10.250 1.1863 0.04683 0.03500 -0.0434 0.3306 1.0000
10.500 1.2015 0.04785 0.03604 -0.0423 0.3230 1.0000
10.750 1.2151 0.04908 0.03730 -0.0413 0.3160 1.0000
11.000 1.2124 0.05143 0.03981 -0.0395 0.3085 1.0000
11.250 1.2482 0.05110 0.03938 -0.0395 0.3021 1.0000
11.500 1.2245 0.05513 0.04368 -0.0371 0.2952 1.0000
11.750 1.2317 0.05690 0.04552 -0.0360 0.2886 1.0000
12.000 1.2563 0.05735 0.04594 -0.0355 0.2831 1.0000
12.250 1.2147 0.06359 0.05250 -0.0337 0.2762 1.0000
12.500 1.2243 0.06532 0.05431 -0.0330 0.2707 1.0000
12.750 1.2428 0.06622 0.05521 -0.0323 0.2658 1.0000
13.000 1.1393 0.08123 0.07061 -0.0335 0.2564 1.0000
13.250 1.1704 0.08020 0.06960 -0.0323 0.2527 1.0000
13.500 1.0454 0.10259 0.09221 -0.0390 0.2381 1.0000
13.750 1.0702 0.10196 0.09162 -0.0378 0.2356 1.0000
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Polar data table (+)
Polar graphs
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