WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 100,000 Max Cl/Cd: 51.64 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb13535sm-il-100000-n5.txt Download as CSV file: xf-wb13535sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WB-135/35 13.5% smoothed
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4270 0.09037 0.08546 -0.0553 1.0000 0.0245
-11.250 -0.5203 0.06845 0.06317 -0.0706 1.0000 0.0216
-11.000 -0.5404 0.06300 0.05766 -0.0738 1.0000 0.0215
-10.750 -0.5595 0.05845 0.05306 -0.0761 1.0000 0.0214
-10.500 -0.5822 0.05469 0.04924 -0.0774 1.0000 0.0214
-10.250 -0.6063 0.05229 0.04686 -0.0756 1.0000 0.0212
-10.000 -0.6344 0.05077 0.04530 -0.0713 1.0000 0.0212
-9.750 -0.6369 0.04723 0.04140 -0.0733 0.9930 0.0214
-9.500 -0.6230 0.04310 0.03699 -0.0768 0.9836 0.0222
-9.250 -0.6031 0.04004 0.03370 -0.0793 0.9754 0.0228
-9.000 -0.5830 0.03745 0.03088 -0.0808 0.9665 0.0235
-8.750 -0.5601 0.03513 0.02830 -0.0822 0.9588 0.0242
-8.500 -0.5347 0.03300 0.02593 -0.0835 0.9518 0.0253
-8.250 -0.5102 0.03121 0.02391 -0.0843 0.9442 0.0268
-8.000 -0.4816 0.02969 0.02214 -0.0855 0.9378 0.0287
-7.750 -0.4572 0.02795 0.02028 -0.0862 0.9309 0.0308
-7.500 -0.4325 0.02656 0.01878 -0.0867 0.9234 0.0328
-7.250 -0.4056 0.02531 0.01733 -0.0873 0.9169 0.0357
-7.000 -0.3821 0.02407 0.01592 -0.0873 0.9087 0.0399
-6.750 -0.3545 0.02283 0.01450 -0.0880 0.9027 0.0462
-6.500 -0.3328 0.02161 0.01321 -0.0876 0.8941 0.0569
-6.250 -0.3076 0.02002 0.01198 -0.0881 0.8885 0.1093
-6.000 -0.2835 0.01962 0.01160 -0.0877 0.8799 0.1634
-5.750 -0.2512 0.01942 0.01126 -0.0887 0.8750 0.1941
-5.500 -0.2278 0.01945 0.01123 -0.0880 0.8663 0.2197
-5.250 -0.1978 0.01943 0.01104 -0.0885 0.8610 0.2420
-5.000 -0.1729 0.01930 0.01083 -0.0879 0.8536 0.2530
-4.750 -0.1439 0.01901 0.01040 -0.0881 0.8477 0.2615
-4.500 -0.1155 0.01876 0.01001 -0.0881 0.8419 0.2704
-4.250 -0.0896 0.01856 0.00973 -0.0877 0.8350 0.2783
-4.000 -0.0590 0.01830 0.00931 -0.0881 0.8306 0.2883
-3.750 -0.0348 0.01817 0.00914 -0.0875 0.8235 0.2971
-3.500 -0.0067 0.01798 0.00887 -0.0875 0.8179 0.3075
-3.250 0.0224 0.01779 0.00857 -0.0876 0.8132 0.3189
-3.000 0.0464 0.01770 0.00847 -0.0869 0.8064 0.3295
-2.750 0.0751 0.01754 0.00827 -0.0870 0.8017 0.3421
-2.500 0.1012 0.01745 0.00813 -0.0866 0.7961 0.3548
-2.250 0.1269 0.01738 0.00804 -0.0862 0.7902 0.3679
-2.000 0.1560 0.01725 0.00787 -0.0863 0.7859 0.3826
-1.750 0.1806 0.01724 0.00787 -0.0857 0.7799 0.3974
-1.500 0.2072 0.01716 0.00779 -0.0854 0.7738 0.4128
-1.250 0.2352 0.01703 0.00764 -0.0851 0.7670 0.4294
-1.000 0.2611 0.01690 0.00752 -0.0845 0.7580 0.4464
-0.750 0.2872 0.01677 0.00739 -0.0839 0.7486 0.4642
-0.500 0.3165 0.01658 0.00717 -0.0837 0.7401 0.4846
-0.250 0.3406 0.01653 0.00714 -0.0829 0.7300 0.5046
0.000 0.3693 0.01638 0.00701 -0.0827 0.7222 0.5270
0.250 0.3947 0.01634 0.00702 -0.0821 0.7138 0.5508
0.500 0.4229 0.01623 0.00696 -0.0820 0.7075 0.5776
0.750 0.4473 0.01617 0.00702 -0.0812 0.6995 0.6080
1.000 0.4754 0.01597 0.00695 -0.0810 0.6930 0.6483
1.250 0.4999 0.01576 0.00704 -0.0801 0.6843 0.7098
1.500 0.5916 0.01524 0.00701 -0.0929 0.6751 0.9995
1.750 0.6160 0.01533 0.00702 -0.0922 0.6663 1.0000
2.000 0.6385 0.01546 0.00710 -0.0911 0.6565 1.0000
2.250 0.6632 0.01554 0.00708 -0.0904 0.6473 1.0000
2.500 0.6856 0.01566 0.00718 -0.0892 0.6364 1.0000
2.750 0.7078 0.01579 0.00730 -0.0881 0.6251 1.0000
3.000 0.7306 0.01591 0.00737 -0.0870 0.6134 1.0000
3.250 0.7532 0.01601 0.00746 -0.0858 0.6004 1.0000
3.500 0.7752 0.01614 0.00756 -0.0846 0.5860 1.0000
3.750 0.7964 0.01628 0.00768 -0.0832 0.5699 1.0000
4.000 0.8172 0.01644 0.00783 -0.0817 0.5525 1.0000
4.250 0.8380 0.01661 0.00796 -0.0803 0.5328 1.0000
4.500 0.8581 0.01681 0.00810 -0.0787 0.5111 1.0000
4.750 0.8777 0.01706 0.00827 -0.0770 0.4878 1.0000
5.000 0.8969 0.01737 0.00847 -0.0754 0.4652 1.0000
5.250 0.9158 0.01774 0.00873 -0.0737 0.4449 1.0000
5.500 0.9345 0.01816 0.00904 -0.0720 0.4274 1.0000
5.750 0.9532 0.01862 0.00942 -0.0704 0.4120 1.0000
6.000 0.9723 0.01909 0.00983 -0.0690 0.3987 1.0000
6.250 0.9918 0.01957 0.01028 -0.0676 0.3870 1.0000
6.500 1.0116 0.02006 0.01075 -0.0663 0.3771 1.0000
6.750 1.0317 0.02057 0.01125 -0.0650 0.3680 1.0000
7.000 1.0520 0.02107 0.01181 -0.0639 0.3594 1.0000
7.250 1.0704 0.02162 0.01232 -0.0624 0.3489 1.0000
7.500 1.0853 0.02219 0.01285 -0.0604 0.3355 1.0000
7.750 1.0986 0.02273 0.01343 -0.0581 0.3220 1.0000
8.000 1.1118 0.02326 0.01402 -0.0559 0.3104 1.0000
8.250 1.1257 0.02380 0.01461 -0.0537 0.3009 1.0000
8.500 1.1344 0.02440 0.01525 -0.0508 0.2876 1.0000
8.750 1.1424 0.02506 0.01593 -0.0480 0.2738 1.0000
9.000 1.1524 0.02573 0.01668 -0.0456 0.2615 1.0000
9.250 1.1617 0.02646 0.01749 -0.0432 0.2476 1.0000
9.500 1.1689 0.02732 0.01841 -0.0408 0.2294 1.0000
9.750 1.1755 0.02831 0.01943 -0.0385 0.2057 1.0000
10.000 1.1780 0.02965 0.02066 -0.0359 0.1735 1.0000
10.250 1.1717 0.03179 0.02244 -0.0330 0.1234 1.0000
10.500 1.1484 0.03563 0.02557 -0.0295 0.0487 1.0000
10.750 1.1410 0.03841 0.02821 -0.0273 0.0320 1.0000
11.000 1.1409 0.04064 0.03051 -0.0258 0.0283 1.0000
11.250 1.1387 0.04315 0.03316 -0.0244 0.0258 1.0000
11.500 1.1377 0.04563 0.03577 -0.0232 0.0247 1.0000
11.750 1.1363 0.04826 0.03858 -0.0223 0.0240 1.0000
12.000 1.1322 0.05127 0.04178 -0.0216 0.0231 1.0000
12.250 1.1283 0.05438 0.04506 -0.0211 0.0227 1.0000
12.500 1.1221 0.05789 0.04875 -0.0210 0.0223 1.0000
12.750 1.1132 0.06192 0.05296 -0.0212 0.0217 1.0000
13.000 1.1034 0.06629 0.05751 -0.0217 0.0213 1.0000
13.250 1.0920 0.07111 0.06249 -0.0226 0.0207 1.0000
13.500 1.0811 0.07612 0.06767 -0.0239 0.0205 1.0000
13.750 1.0703 0.08134 0.07304 -0.0253 0.0203 1.0000
14.000 1.0576 0.08703 0.07887 -0.0271 0.0198 1.0000
14.250 1.0492 0.09212 0.08409 -0.0288 0.0196 1.0000
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Polar data table (+)
Polar graphs
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