FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: FX 61-184 AIRFOIL (fx61184-il) Reynolds number: 100,000 Max Cl/Cd: 43.42 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61184-il-100000-n5.txt Download as CSV file: xf-fx61184-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-184 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4496 0.09525 0.09013 -0.0732 1.0000 0.0277
-13.250 -0.4828 0.08569 0.08048 -0.0787 1.0000 0.0271
-13.000 -0.5122 0.07851 0.07319 -0.0823 1.0000 0.0266
-12.750 -0.5406 0.07272 0.06729 -0.0845 1.0000 0.0265
-12.500 -0.5666 0.06829 0.06277 -0.0851 1.0000 0.0264
-12.250 -0.5776 0.06255 0.05677 -0.0897 0.9739 0.0269
-12.000 -0.5841 0.05745 0.05133 -0.0942 0.9539 0.0272
-11.750 -0.5845 0.05272 0.04616 -0.0989 0.9396 0.0279
-11.500 -0.5783 0.04837 0.04129 -0.1032 0.9281 0.0285
-11.250 -0.5643 0.04482 0.03730 -0.1063 0.9172 0.0291
-11.000 -0.5394 0.04233 0.03463 -0.1087 0.9091 0.0298
-10.750 -0.5146 0.04032 0.03245 -0.1109 0.9011 0.0309
-10.500 -0.4920 0.03857 0.03049 -0.1124 0.8930 0.0324
-10.250 -0.4686 0.03684 0.02843 -0.1134 0.8854 0.0344
-10.000 -0.4400 0.03529 0.02660 -0.1141 0.8792 0.0356
-9.750 -0.4109 0.03409 0.02541 -0.1143 0.8731 0.0370
-9.500 -0.3843 0.03307 0.02432 -0.1149 0.8676 0.0390
-9.250 -0.3610 0.03224 0.02335 -0.1147 0.8616 0.0414
-9.000 -0.3363 0.03146 0.02248 -0.1143 0.8559 0.0439
-8.750 -0.3129 0.03063 0.02167 -0.1143 0.8510 0.0463
-8.500 -0.2954 0.02994 0.02095 -0.1134 0.8450 0.0488
-8.250 -0.2772 0.02929 0.02019 -0.1127 0.8394 0.0529
-8.000 -0.2621 0.02839 0.01930 -0.1121 0.8346 0.0572
-7.750 -0.2516 0.02771 0.01858 -0.1105 0.8287 0.0622
-7.500 -0.2426 0.02691 0.01779 -0.1088 0.8230 0.0677
-7.250 -0.2317 0.02618 0.01701 -0.1074 0.8185 0.0771
-7.000 -0.2289 0.02548 0.01638 -0.1049 0.8126 0.0881
-6.750 -0.2238 0.02456 0.01561 -0.1031 0.8072 0.1092
-6.500 -0.2195 0.02323 0.01457 -0.1019 0.8027 0.1597
-6.250 -0.2232 0.02166 0.01359 -0.1000 0.7968 0.2584
-6.000 -0.2154 0.02090 0.01369 -0.0980 0.7918 0.3973
-5.750 -0.1880 0.02209 0.01515 -0.0957 0.7885 0.4742
-5.250 -0.1395 0.02309 0.01587 -0.0945 0.7802 0.5371
-5.000 -0.1133 0.02460 0.01730 -0.0924 0.7760 0.5597
-4.750 -0.0857 0.02575 0.01833 -0.0908 0.7725 0.5748
-4.500 -0.0569 0.02614 0.01856 -0.0902 0.7697 0.5812
-4.250 -0.0392 0.02598 0.01829 -0.0895 0.7644 0.5896
-4.000 -0.0158 0.02623 0.01845 -0.0883 0.7600 0.5934
-3.750 0.0099 0.02576 0.01776 -0.0894 0.7563 0.6033
-3.500 0.0381 0.02588 0.01777 -0.0890 0.7535 0.6060
-3.250 0.0565 0.02609 0.01795 -0.0873 0.7483 0.6094
-3.000 0.0792 0.02600 0.01776 -0.0870 0.7437 0.6148
-2.750 0.1069 0.02565 0.01726 -0.0880 0.7401 0.6211
-2.500 0.1351 0.02565 0.01716 -0.0879 0.7374 0.6237
-2.250 0.1531 0.02578 0.01727 -0.0865 0.7319 0.6273
-2.000 0.1773 0.02562 0.01702 -0.0867 0.7272 0.6326
-1.750 0.2063 0.02536 0.01664 -0.0877 0.7237 0.6373
-1.500 0.2352 0.02530 0.01650 -0.0878 0.7210 0.6397
-1.250 0.2516 0.02548 0.01670 -0.0862 0.7149 0.6428
-1.000 0.2766 0.02540 0.01657 -0.0863 0.7103 0.6466
-0.750 0.3103 0.02504 0.01606 -0.0886 0.7069 0.6521
-0.500 0.3401 0.02493 0.01590 -0.0889 0.7043 0.6540
-0.250 0.3531 0.02523 0.01626 -0.0868 0.6971 0.6564
0.000 0.3793 0.02518 0.01619 -0.0867 0.6929 0.6590
0.250 0.4106 0.02501 0.01595 -0.0877 0.6899 0.6621
0.500 0.4352 0.02503 0.01595 -0.0881 0.6847 0.6661
0.750 0.4593 0.02506 0.01597 -0.0883 0.6791 0.6691
1.000 0.4870 0.02498 0.01589 -0.0884 0.6755 0.6710
1.250 0.5186 0.02483 0.01570 -0.0890 0.6728 0.6733
1.500 0.5321 0.02520 0.01615 -0.0873 0.6651 0.6760
1.750 0.5608 0.02512 0.01607 -0.0879 0.6609 0.6787
2.000 0.5959 0.02488 0.01579 -0.0896 0.6579 0.6817
2.250 0.6151 0.02516 0.01611 -0.0891 0.6509 0.6848
2.500 0.6390 0.02520 0.01620 -0.0886 0.6459 0.6867
2.750 0.6705 0.02502 0.01603 -0.0893 0.6427 0.6887
3.000 0.6886 0.02532 0.01640 -0.0883 0.6362 0.6909
3.250 0.7132 0.02540 0.01652 -0.0882 0.6307 0.6934
3.500 0.7473 0.02519 0.01632 -0.0895 0.6273 0.6964
3.750 0.7685 0.02549 0.01667 -0.0893 0.6207 0.6995
4.000 0.7925 0.02555 0.01681 -0.0890 0.6150 0.7015
4.250 0.8255 0.02529 0.01658 -0.0898 0.6115 0.7032
4.500 0.8388 0.02574 0.01714 -0.0880 0.6035 0.7053
4.750 0.8669 0.02566 0.01713 -0.0882 0.5983 0.7078
5.000 0.9039 0.02531 0.01680 -0.0897 0.5949 0.7106
5.250 0.9134 0.02596 0.01756 -0.0877 0.5857 0.7136
5.500 0.9499 0.02562 0.01726 -0.0892 0.5808 0.7163
5.750 0.9621 0.02601 0.01778 -0.0871 0.5722 0.7182
6.000 0.9923 0.02578 0.01761 -0.0874 0.5661 0.7202
6.250 1.0083 0.02606 0.01799 -0.0859 0.5577 0.7226
6.500 1.0385 0.02583 0.01783 -0.0863 0.5504 0.7254
6.750 1.0518 0.02617 0.01826 -0.0844 0.5408 0.7286
7.000 1.0884 0.02586 0.01797 -0.0859 0.5335 0.7318
7.250 1.0937 0.02646 0.01873 -0.0829 0.5237 0.7341
7.500 1.1270 0.02618 0.01850 -0.0836 0.5167 0.7364
7.750 1.1335 0.02689 0.01935 -0.0809 0.5060 0.7391
8.000 1.1525 0.02719 0.01974 -0.0800 0.4962 0.7421
8.250 1.1796 0.02717 0.01977 -0.0801 0.4862 0.7454
8.500 1.1877 0.02797 0.02069 -0.0780 0.4739 0.7487
8.750 1.1990 0.02858 0.02140 -0.0761 0.4619 0.7516
9.000 1.2134 0.02911 0.02199 -0.0747 0.4494 0.7549
9.250 1.2279 0.02969 0.02264 -0.0735 0.4362 0.7583
9.500 1.2415 0.03039 0.02338 -0.0723 0.4223 0.7618
9.750 1.2519 0.03127 0.02432 -0.0709 0.4078 0.7649
10.000 1.2586 0.03234 0.02545 -0.0691 0.3922 0.7681
10.250 1.2635 0.03363 0.02677 -0.0673 0.3752 0.7718
10.500 1.2680 0.03507 0.02824 -0.0658 0.3573 0.7760
10.750 1.2723 0.03660 0.02979 -0.0643 0.3387 0.7802
11.000 1.2746 0.03822 0.03142 -0.0626 0.3199 0.7840
11.250 1.2767 0.03997 0.03314 -0.0612 0.3012 0.7882
11.500 1.2782 0.04193 0.03506 -0.0599 0.2823 0.7926
11.750 1.2780 0.04409 0.03721 -0.0587 0.2635 0.7968
12.000 1.2773 0.04631 0.03943 -0.0575 0.2460 0.8010
12.250 1.2771 0.04864 0.04176 -0.0565 0.2297 0.8060
12.500 1.2771 0.05110 0.04424 -0.0558 0.2143 0.8114
12.750 1.2762 0.05360 0.04678 -0.0550 0.2000 0.8169
13.000 1.2753 0.05629 0.04950 -0.0544 0.1860 0.8235
13.250 1.2740 0.05905 0.05230 -0.0539 0.1731 0.8304
13.500 1.2721 0.06197 0.05526 -0.0535 0.1605 0.8386
13.750 1.2693 0.06501 0.05836 -0.0531 0.1482 0.8479
14.000 1.2665 0.06811 0.06152 -0.0529 0.1362 0.8597
14.250 1.2628 0.07112 0.06464 -0.0524 0.1255 0.8765
14.750 1.2499 0.07770 0.07132 -0.0519 0.1074 1.0000
15.000 1.2495 0.08147 0.07516 -0.0529 0.0979 1.0000
15.250 1.2483 0.08537 0.07910 -0.0540 0.0901 1.0000
15.500 1.2454 0.08955 0.08328 -0.0553 0.0834 1.0000
15.750 1.2455 0.09338 0.08719 -0.0565 0.0772 1.0000
16.000 1.2431 0.09758 0.09142 -0.0579 0.0722 1.0000
16.250 1.2427 0.10147 0.09536 -0.0592 0.0679 1.0000
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