WORTMANN FX 05-191 AIRFOIL (fx05191-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 05-191 AIRFOIL (fx05191-il) Reynolds number: 200,000 Max Cl/Cd: 55.65 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx05191-il-200000.txt Download as CSV file: xf-fx05191-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 05-191 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.2958 0.12635 0.12265 -0.0884 0.9759 0.0732
-13.500 -0.2871 0.12237 0.11866 -0.0913 0.9745 0.0757
-13.250 -0.3633 0.10345 0.09977 -0.1111 0.9723 0.0812
-13.000 -0.3176 0.10477 0.10112 -0.1056 0.9719 0.0830
-12.750 -0.3005 0.10383 0.10017 -0.1045 0.9694 0.0843
-12.500 -0.2087 0.08479 0.08125 -0.1215 0.9593 0.0964
-12.250 -0.1768 0.08446 0.08089 -0.1210 0.9587 0.0981
-11.500 -0.5047 0.03749 0.03219 -0.1275 0.9446 0.0486
-11.250 -0.5684 0.05371 0.04850 -0.1244 0.9435 0.0604
-11.000 -0.6118 0.04908 0.04334 -0.1143 0.9337 0.0480
-10.750 -0.6030 0.04551 0.03947 -0.1143 0.9312 0.0469
-10.500 -0.6254 0.04503 0.03887 -0.1069 0.9241 0.0466
-10.250 -0.6321 0.04332 0.03693 -0.1025 0.9188 0.0462
-10.000 -0.6166 0.04057 0.03383 -0.1022 0.9164 0.0457
-9.750 -0.5898 0.03838 0.03135 -0.1035 0.9150 0.0465
-9.500 -0.6222 0.03883 0.03176 -0.0933 0.9058 0.0464
-9.250 -0.6032 0.03726 0.02997 -0.0926 0.9026 0.0471
-9.000 -0.5724 0.03552 0.02796 -0.0938 0.9008 0.0479
-8.750 -0.5334 0.03378 0.02599 -0.0962 0.8999 0.0486
-8.500 -0.4901 0.03233 0.02432 -0.0994 0.8992 0.0494
-8.250 -0.4854 0.03174 0.02370 -0.0952 0.8935 0.0501
-8.000 -0.4601 0.03082 0.02286 -0.0947 0.8899 0.0519
-7.750 -0.4211 0.02989 0.02195 -0.0969 0.8880 0.0545
-7.500 -0.3731 0.02888 0.02089 -0.1006 0.8872 0.0573
-7.250 -0.3287 0.02768 0.01971 -0.1038 0.8863 0.0603
-7.000 -0.2987 0.02674 0.01882 -0.1050 0.8843 0.0643
-6.750 -0.3388 0.02737 0.01942 -0.0933 0.8725 0.0636
-6.500 -0.3164 0.02669 0.01870 -0.0931 0.8691 0.0680
-6.250 -0.2938 0.02551 0.01756 -0.0933 0.8667 0.0741
-6.000 -0.2701 0.02452 0.01656 -0.0938 0.8645 0.0835
-5.750 -0.3027 0.02499 0.01698 -0.0833 0.8513 0.0828
-5.500 -0.3063 0.02465 0.01668 -0.0785 0.8437 0.0918
-4.750 -0.2919 0.02031 0.01463 -0.0718 0.8240 0.5303
-4.500 -0.2615 0.02024 0.01467 -0.0722 0.8205 0.5812
-4.250 -0.2240 0.02024 0.01469 -0.0736 0.8187 0.6131
-4.000 -0.1840 0.02037 0.01480 -0.0753 0.8174 0.6399
-3.750 -0.1810 0.02098 0.01542 -0.0707 0.8079 0.6553
-3.500 -0.1561 0.02162 0.01607 -0.0690 0.8038 0.6728
-3.250 -0.1237 0.02251 0.01696 -0.0680 0.8019 0.6886
-3.000 -0.0883 0.02346 0.01790 -0.0672 0.8007 0.6964
-2.750 -0.0696 0.02372 0.01810 -0.0655 0.7950 0.7048
-2.500 -0.0142 0.02360 0.01787 -0.0696 0.7975 0.7071
-2.000 0.0199 0.02366 0.01782 -0.0666 0.7844 0.7201
-1.750 0.0574 0.02364 0.01775 -0.0677 0.7832 0.7222
-1.500 0.0962 0.02358 0.01762 -0.0692 0.7822 0.7251
-1.250 0.0882 0.02375 0.01776 -0.0642 0.7695 0.7356
-1.000 0.1242 0.02370 0.01768 -0.0651 0.7682 0.7377
-0.750 0.1138 0.02433 0.01834 -0.0581 0.7571 0.7419
-0.500 0.1500 0.02407 0.01802 -0.0597 0.7550 0.7472
-0.250 0.1911 0.02366 0.01754 -0.0625 0.7536 0.7534
0.000 0.2269 0.02352 0.01738 -0.0633 0.7523 0.7559
0.250 0.2644 0.02331 0.01714 -0.0647 0.7512 0.7592
0.500 0.3060 0.02294 0.01672 -0.0674 0.7502 0.7646
0.750 0.2907 0.02339 0.01721 -0.0602 0.7379 0.7717
1.000 0.3278 0.02312 0.01692 -0.0614 0.7366 0.7749
1.250 0.3307 0.02343 0.01723 -0.0580 0.7278 0.7837
1.500 0.3563 0.02325 0.01704 -0.0575 0.7241 0.7876
1.750 0.3897 0.02294 0.01673 -0.0580 0.7224 0.7908
2.000 0.4298 0.02255 0.01633 -0.0600 0.7212 0.7951
2.250 0.4800 0.02208 0.01581 -0.0648 0.7202 0.8019
2.500 0.5173 0.02170 0.01545 -0.0660 0.7190 0.8042
2.750 0.4917 0.02234 0.01615 -0.0566 0.7072 0.8108
3.000 0.5409 0.02188 0.01567 -0.0610 0.7059 0.8170
3.250 0.5815 0.02144 0.01524 -0.0630 0.7045 0.8199
3.500 0.5595 0.02207 0.01594 -0.0543 0.6939 0.8262
3.750 0.6029 0.02167 0.01554 -0.0574 0.6920 0.8312
4.000 0.6473 0.02120 0.01508 -0.0605 0.6903 0.8349
4.250 0.6889 0.02081 0.01471 -0.0626 0.6886 0.8378
4.500 0.6721 0.02141 0.01538 -0.0553 0.6786 0.8454
4.750 0.7188 0.02102 0.01499 -0.0591 0.6762 0.8495
5.000 0.7585 0.02060 0.01461 -0.0609 0.6740 0.8522
5.250 0.7578 0.02091 0.01498 -0.0561 0.6667 0.8580
5.500 0.7909 0.02080 0.01490 -0.0576 0.6618 0.8628
5.750 0.8422 0.02025 0.01437 -0.0617 0.6585 0.8657
6.000 0.8507 0.02025 0.01442 -0.0581 0.6517 0.8701
6.250 0.8783 0.01998 0.01418 -0.0581 0.6445 0.8746
6.500 0.9331 0.01957 0.01376 -0.0631 0.6387 0.8777
6.750 0.9293 0.01966 0.01394 -0.0576 0.6297 0.8829
7.000 0.9647 0.01923 0.01349 -0.0586 0.6209 0.8864
7.250 0.9854 0.01896 0.01322 -0.0573 0.6095 0.8909
7.500 0.9966 0.01911 0.01345 -0.0549 0.5995 0.8957
7.750 1.0294 0.01874 0.01304 -0.0555 0.5908 0.8988
8.000 1.0248 0.01903 0.01346 -0.0503 0.5806 0.9042
8.250 1.0485 0.01903 0.01349 -0.0500 0.5706 0.9081
8.500 1.0618 0.01908 0.01359 -0.0478 0.5601 0.9120
8.750 1.0672 0.01931 0.01391 -0.0444 0.5495 0.9164
9.000 1.0817 0.01945 0.01408 -0.0427 0.5369 0.9206
9.250 1.0936 0.01973 0.01439 -0.0408 0.5220 0.9242
9.500 1.0987 0.01999 0.01468 -0.0375 0.5071 0.9283
9.750 1.1025 0.02053 0.01527 -0.0345 0.4895 0.9328
10.000 1.1066 0.02131 0.01609 -0.0321 0.4678 0.9366
10.250 1.1072 0.02196 0.01670 -0.0286 0.4442 0.9407
10.500 1.1052 0.02297 0.01766 -0.0253 0.4127 0.9453
10.750 1.1000 0.02448 0.01898 -0.0221 0.3678 0.9493
11.000 1.0836 0.02649 0.02071 -0.0176 0.3169 0.9539
11.250 1.0651 0.02906 0.02297 -0.0136 0.2643 0.9590
11.500 1.0466 0.03205 0.02565 -0.0103 0.2136 0.9636
11.750 1.0323 0.03505 0.02839 -0.0078 0.1739 0.9684
12.000 1.0256 0.03782 0.03099 -0.0063 0.1457 0.9740
12.250 1.0250 0.04034 0.03341 -0.0057 0.1282 0.9815
12.500 1.0264 0.04263 0.03564 -0.0053 0.1160 1.0000
12.750 1.0341 0.04486 0.03787 -0.0055 0.1062 1.0000
13.000 1.0404 0.04722 0.04022 -0.0056 0.0984 1.0000
13.250 1.0481 0.04951 0.04250 -0.0059 0.0914 1.0000
13.500 1.0570 0.05165 0.04466 -0.0061 0.0851 1.0000
13.750 1.0670 0.05375 0.04676 -0.0065 0.0794 1.0000
14.000 1.0783 0.05564 0.04864 -0.0066 0.0742 1.0000
14.250 1.0914 0.05752 0.05058 -0.0071 0.0697 1.0000
14.500 1.1065 0.05892 0.05186 -0.0070 0.0650 1.0000
14.750 1.1194 0.06093 0.05405 -0.0078 0.0618 1.0000
15.000 1.1333 0.06276 0.05591 -0.0084 0.0585 1.0000
15.250 1.1531 0.06378 0.05682 -0.0084 0.0551 1.0000
15.500 1.1646 0.06599 0.05922 -0.0092 0.0529 1.0000
15.750 1.1775 0.06799 0.06133 -0.0099 0.0504 1.0000
16.000 1.1910 0.06988 0.06321 -0.0106 0.0483 1.0000
16.250 1.2089 0.07130 0.06466 -0.0108 0.0460 1.0000
16.500 1.2186 0.07375 0.06731 -0.0116 0.0443 1.0000
16.750 1.2290 0.07609 0.06978 -0.0123 0.0426 1.0000
17.000 1.2403 0.07830 0.07204 -0.0131 0.0411 1.0000
17.250 1.2605 0.07956 0.07324 -0.0134 0.0393 1.0000
17.500 1.2617 0.08303 0.07698 -0.0144 0.0382 1.0000
17.750 1.2650 0.08630 0.08046 -0.0154 0.0370 1.0000
18.000 1.2696 0.08945 0.08378 -0.0164 0.0359 1.0000
18.250 1.2746 0.09254 0.08700 -0.0176 0.0350 1.0000
18.500 1.2833 0.09511 0.08960 -0.0188 0.0341 1.0000
18.750 1.2943 0.09762 0.09216 -0.0193 0.0330 1.0000
19.000 1.2835 0.10283 0.09768 -0.0213 0.0326 1.0000
19.250 1.2717 0.10838 0.10353 -0.0237 0.0321 1.0000
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Polar graphs
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