CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 200,000 Max Cl/Cd: 70.1 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkysm-il-200000-n5.txt Download as CSV file: xf-clarkysm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4134 0.08708 0.08342 -0.0464 1.0000 0.0225
-9.750 -0.4351 0.08141 0.07784 -0.0473 1.0000 0.0225
-9.500 -0.6058 0.04080 0.03651 -0.0765 0.9825 0.0213
-9.250 -0.6036 0.03510 0.03019 -0.0784 0.9734 0.0218
-9.000 -0.5914 0.03125 0.02577 -0.0791 0.9668 0.0225
-8.750 -0.5735 0.02824 0.02220 -0.0794 0.9608 0.0233
-8.500 -0.5456 0.02677 0.02056 -0.0807 0.9577 0.0243
-8.250 -0.5226 0.02591 0.01960 -0.0805 0.9516 0.0251
-8.000 -0.4960 0.02474 0.01823 -0.0810 0.9470 0.0263
-7.750 -0.4669 0.02319 0.01635 -0.0819 0.9440 0.0276
-7.500 -0.4408 0.02189 0.01481 -0.0821 0.9393 0.0286
-7.250 -0.4150 0.02110 0.01397 -0.0821 0.9337 0.0297
-7.000 -0.3833 0.02037 0.01313 -0.0832 0.9302 0.0315
-6.750 -0.3504 0.01947 0.01201 -0.0844 0.9275 0.0338
-6.500 -0.3276 0.01881 0.01133 -0.0836 0.9202 0.0353
-6.250 -0.2975 0.01817 0.01061 -0.0842 0.9157 0.0374
-6.000 -0.2644 0.01748 0.00977 -0.0853 0.9123 0.0402
-5.750 -0.2403 0.01698 0.00926 -0.0846 0.9050 0.0427
-5.500 -0.2102 0.01648 0.00869 -0.0851 0.8998 0.0460
-5.250 -0.1774 0.01589 0.00804 -0.0861 0.8961 0.0499
-5.000 -0.1537 0.01556 0.00769 -0.0853 0.8877 0.0537
-4.750 -0.1231 0.01509 0.00713 -0.0858 0.8825 0.0581
-4.500 -0.0960 0.01472 0.00677 -0.0856 0.8757 0.0631
-4.250 -0.0680 0.01439 0.00636 -0.0855 0.8688 0.0685
-4.000 -0.0384 0.01400 0.00597 -0.0859 0.8629 0.0750
-3.750 -0.0131 0.01373 0.00565 -0.0852 0.8547 0.0815
-3.500 0.0174 0.01339 0.00529 -0.0857 0.8490 0.0902
-3.250 0.0413 0.01313 0.00504 -0.0848 0.8398 0.0987
-3.000 0.0709 0.01284 0.00474 -0.0850 0.8334 0.1104
-2.750 0.0951 0.01262 0.00454 -0.0842 0.8242 0.1246
-2.500 0.1236 0.01233 0.00429 -0.0842 0.8172 0.1466
-2.250 0.1476 0.01209 0.00415 -0.0834 0.8074 0.1750
-2.000 0.1744 0.01184 0.00399 -0.0831 0.7993 0.2149
-1.750 0.1993 0.01161 0.00387 -0.0824 0.7897 0.2566
-1.500 0.2242 0.01138 0.00376 -0.0818 0.7800 0.3030
-1.250 0.2495 0.01113 0.00362 -0.0811 0.7694 0.3578
-1.000 0.2719 0.01083 0.00353 -0.0799 0.7567 0.4305
-0.750 0.2924 0.01045 0.00348 -0.0782 0.7443 0.5323
-0.500 0.3117 0.01000 0.00348 -0.0761 0.7333 0.6681
0.000 0.4308 0.00969 0.00363 -0.0881 0.7108 0.9419
0.250 0.4742 0.00979 0.00363 -0.0911 0.6986 0.9688
0.500 0.5147 0.00988 0.00361 -0.0937 0.6862 0.9842
0.750 0.5564 0.00995 0.00356 -0.0966 0.6732 0.9956
1.250 0.6098 0.01011 0.00353 -0.0962 0.6464 1.0000
1.500 0.6311 0.01021 0.00355 -0.0948 0.6324 1.0000
1.750 0.6523 0.01033 0.00358 -0.0933 0.6184 1.0000
2.000 0.6736 0.01045 0.00362 -0.0919 0.6045 1.0000
2.250 0.6946 0.01059 0.00368 -0.0905 0.5893 1.0000
2.500 0.7155 0.01075 0.00375 -0.0890 0.5736 1.0000
2.750 0.7362 0.01092 0.00384 -0.0875 0.5576 1.0000
3.000 0.7568 0.01110 0.00395 -0.0859 0.5417 1.0000
3.250 0.7773 0.01129 0.00406 -0.0844 0.5257 1.0000
3.500 0.7974 0.01150 0.00420 -0.0828 0.5090 1.0000
3.750 0.8172 0.01173 0.00434 -0.0811 0.4917 1.0000
4.000 0.8367 0.01198 0.00452 -0.0794 0.4746 1.0000
4.250 0.8562 0.01224 0.00470 -0.0777 0.4583 1.0000
4.500 0.8758 0.01250 0.00490 -0.0761 0.4429 1.0000
4.750 0.8952 0.01277 0.00513 -0.0744 0.4279 1.0000
5.000 0.9144 0.01306 0.00536 -0.0727 0.4135 1.0000
5.250 0.9332 0.01337 0.00560 -0.0709 0.3985 1.0000
5.500 0.9512 0.01370 0.00586 -0.0691 0.3823 1.0000
5.750 0.9687 0.01405 0.00615 -0.0671 0.3659 1.0000
6.000 0.9864 0.01440 0.00644 -0.0652 0.3507 1.0000
6.250 1.0044 0.01475 0.00674 -0.0634 0.3371 1.0000
6.500 1.0225 0.01509 0.00705 -0.0617 0.3250 1.0000
6.750 1.0400 0.01546 0.00739 -0.0598 0.3131 1.0000
7.000 1.0569 0.01584 0.00773 -0.0579 0.3012 1.0000
7.250 1.0753 0.01617 0.00808 -0.0562 0.2907 1.0000
7.500 1.0923 0.01654 0.00846 -0.0543 0.2808 1.0000
7.750 1.1076 0.01693 0.00884 -0.0521 0.2708 1.0000
8.000 1.1241 0.01728 0.00922 -0.0501 0.2606 1.0000
8.250 1.1392 0.01768 0.00963 -0.0480 0.2504 1.0000
8.500 1.1534 0.01812 0.01008 -0.0457 0.2382 1.0000
8.750 1.1674 0.01859 0.01055 -0.0435 0.2245 1.0000
9.000 1.1810 0.01910 0.01106 -0.0413 0.2075 1.0000
9.250 1.1928 0.01973 0.01164 -0.0389 0.1863 1.0000
9.500 1.2011 0.02056 0.01235 -0.0362 0.1594 1.0000
9.750 1.2070 0.02160 0.01324 -0.0333 0.1337 1.0000
10.000 1.2135 0.02267 0.01421 -0.0306 0.1168 1.0000
10.250 1.2212 0.02370 0.01522 -0.0282 0.1059 1.0000
10.500 1.2292 0.02475 0.01627 -0.0259 0.0985 1.0000
10.750 1.2377 0.02580 0.01736 -0.0238 0.0928 1.0000
11.000 1.2439 0.02702 0.01860 -0.0217 0.0881 1.0000
11.250 1.2533 0.02808 0.01976 -0.0199 0.0839 1.0000
11.500 1.2601 0.02934 0.02107 -0.0180 0.0802 1.0000
11.750 1.2642 0.03085 0.02261 -0.0161 0.0771 1.0000
12.000 1.2720 0.03215 0.02400 -0.0146 0.0744 1.0000
12.250 1.2794 0.03352 0.02548 -0.0132 0.0717 1.0000
12.500 1.2850 0.03508 0.02712 -0.0118 0.0690 1.0000
12.750 1.2878 0.03692 0.02900 -0.0104 0.0668 1.0000
13.000 1.2908 0.03881 0.03096 -0.0092 0.0646 1.0000
13.250 1.2973 0.04047 0.03275 -0.0083 0.0624 1.0000
13.500 1.3023 0.04230 0.03469 -0.0074 0.0602 1.0000
13.750 1.3057 0.04434 0.03681 -0.0066 0.0581 1.0000
14.000 1.3063 0.04672 0.03924 -0.0060 0.0562 1.0000
14.250 1.3074 0.04913 0.04173 -0.0054 0.0545 1.0000
14.500 1.3116 0.05129 0.04404 -0.0051 0.0526 1.0000
14.750 1.3141 0.05370 0.04657 -0.0048 0.0508 1.0000
15.000 1.3156 0.05630 0.04927 -0.0048 0.0491 1.0000
15.250 1.3142 0.05931 0.05234 -0.0049 0.0474 1.0000
15.500 1.3120 0.06248 0.05557 -0.0051 0.0459 1.0000
15.750 1.3137 0.06529 0.05854 -0.0054 0.0442 1.0000
16.000 1.3136 0.06838 0.06178 -0.0058 0.0426 1.0000
16.250 1.3124 0.07169 0.06520 -0.0065 0.0412 1.0000
16.500 1.3092 0.07535 0.06895 -0.0074 0.0399 1.0000
16.750 1.3040 0.07936 0.07302 -0.0085 0.0387 1.0000
17.000 1.3020 0.08300 0.07680 -0.0094 0.0374 1.0000
17.250 1.2994 0.08679 0.08074 -0.0105 0.0361 1.0000
17.500 1.2955 0.09083 0.08490 -0.0119 0.0348 1.0000
17.750 1.2906 0.09513 0.08930 -0.0134 0.0337 1.0000
18.000 1.2843 0.09972 0.09397 -0.0153 0.0327 1.0000
18.250 1.2777 0.10431 0.09863 -0.0170 0.0319 1.0000
18.500 1.2733 0.10868 0.10316 -0.0188 0.0308 1.0000
18.750 1.2679 0.11327 0.10790 -0.0207 0.0297 1.0000
19.000 1.2617 0.11810 0.11286 -0.0230 0.0287 1.0000
19.250 1.2552 0.12303 0.11789 -0.0253 0.0278 1.0000
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Polar data table (+)
Polar graphs
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