WB-140/35/FB 14% (wb140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-140/35/FB 14% (wb140-il) Reynolds number: 200,000 Max Cl/Cd: 83.95 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb140-il-200000.txt Download as CSV file: xf-wb140-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WB-140/35/FB 14%
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0277 0.09709 0.09360 -0.0994 0.9043 0.0675
-10.500 -0.0514 0.09346 0.09003 -0.1050 0.8989 0.0713
-10.250 -0.0426 0.08896 0.08551 -0.1041 0.8952 0.0730
-10.000 -0.0221 0.08714 0.08366 -0.1022 0.8919 0.0757
-9.750 -0.0164 0.08445 0.08094 -0.1025 0.8891 0.0799
-9.500 -0.0467 0.08002 0.07658 -0.1100 0.8841 0.0846
-9.250 -0.0284 0.07620 0.07275 -0.1074 0.8815 0.0867
-9.000 -0.0089 0.07455 0.07106 -0.1058 0.8787 0.0905
-8.750 -0.1046 0.07990 0.07636 -0.1097 0.8853 0.0865
-8.500 -0.0836 0.07873 0.07516 -0.1073 0.8822 0.0895
-8.250 -0.0064 0.06434 0.06088 -0.1095 0.8699 0.1023
-8.000 -0.0025 0.06133 0.05787 -0.1105 0.8663 0.1058
-7.750 -0.0290 0.05585 0.05246 -0.1164 0.8616 0.1116
-7.500 -0.1499 0.03728 0.03245 -0.1428 0.8615 0.0574
-7.250 -0.1402 0.03180 0.02581 -0.1426 0.8587 0.0490
-7.000 -0.1180 0.02973 0.02348 -0.1424 0.8562 0.0479
-6.750 -0.0994 0.02713 0.02058 -0.1419 0.8527 0.0465
-6.500 -0.0768 0.02538 0.01852 -0.1415 0.8498 0.0458
-6.250 -0.0520 0.02399 0.01689 -0.1412 0.8473 0.0456
-6.000 -0.0258 0.02296 0.01567 -0.1411 0.8452 0.0467
-5.750 0.0016 0.02216 0.01470 -0.1411 0.8433 0.0480
-5.500 0.0291 0.02130 0.01372 -0.1410 0.8417 0.0484
-5.250 0.0513 0.02056 0.01297 -0.1405 0.8385 0.0491
-5.000 0.0740 0.01995 0.01237 -0.1400 0.8349 0.0508
-4.750 0.0997 0.01954 0.01192 -0.1399 0.8320 0.0535
-4.500 0.1274 0.01921 0.01148 -0.1399 0.8296 0.0554
-4.250 0.1568 0.01888 0.01101 -0.1402 0.8275 0.0575
-4.000 0.1872 0.01856 0.01057 -0.1405 0.8255 0.0607
-3.750 0.2084 0.01863 0.01069 -0.1397 0.8205 0.0683
-3.500 0.2345 0.01831 0.01057 -0.1396 0.8165 0.1324
-3.250 0.2664 0.01908 0.01106 -0.1397 0.8132 0.1742
-3.000 0.2981 0.01907 0.01070 -0.1402 0.8105 0.1891
-2.750 0.3216 0.01841 0.01022 -0.1399 0.8060 0.2007
-2.500 0.3454 0.01801 0.00997 -0.1395 0.8008 0.2097
-2.250 0.3742 0.01778 0.00988 -0.1397 0.7972 0.2230
-2.000 0.4056 0.01772 0.00974 -0.1402 0.7946 0.2350
-1.750 0.4317 0.01785 0.00980 -0.1400 0.7906 0.2411
-1.500 0.4555 0.01795 0.00991 -0.1395 0.7854 0.2459
-1.250 0.4838 0.01790 0.00984 -0.1397 0.7821 0.2535
-1.000 0.5137 0.01774 0.00971 -0.1401 0.7797 0.2628
-0.750 0.5449 0.01761 0.00955 -0.1407 0.7776 0.2720
-0.500 0.5646 0.01798 0.01000 -0.1398 0.7720 0.2775
-0.250 0.5920 0.01796 0.00998 -0.1398 0.7681 0.2793
0.000 0.6226 0.01778 0.00977 -0.1402 0.7652 0.2806
0.250 0.6551 0.01756 0.00950 -0.1410 0.7629 0.2820
0.500 0.6760 0.01789 0.00988 -0.1401 0.7569 0.2834
0.750 0.7042 0.01785 0.00985 -0.1402 0.7530 0.2851
1.000 0.7356 0.01766 0.00967 -0.1408 0.7502 0.2875
1.250 0.7674 0.01749 0.00950 -0.1414 0.7473 0.2909
1.500 0.7892 0.01772 0.00979 -0.1405 0.7403 0.2946
1.750 0.8220 0.01738 0.00944 -0.1412 0.7358 0.3008
2.000 0.8520 0.01722 0.00932 -0.1414 0.7305 0.3116
2.250 0.8778 0.01722 0.00942 -0.1411 0.7236 0.3349
2.500 0.9101 0.01688 0.00926 -0.1419 0.7191 0.4090
2.750 0.9288 0.01641 0.00966 -0.1403 0.7121 0.6939
3.000 0.9588 0.01592 0.00963 -0.1400 0.7064 1.0000
3.250 0.9864 0.01606 0.00973 -0.1400 0.7006 1.0000
3.500 1.0104 0.01620 0.00990 -0.1393 0.6929 1.0000
3.750 1.0385 0.01620 0.00986 -0.1393 0.6865 1.0000
4.000 1.0610 0.01620 0.00990 -0.1382 0.6774 1.0000
4.250 1.0839 0.01614 0.00987 -0.1373 0.6685 1.0000
4.500 1.1106 0.01589 0.00964 -0.1369 0.6606 1.0000
4.750 1.1304 0.01585 0.00969 -0.1354 0.6502 1.0000
5.000 1.1547 0.01564 0.00951 -0.1347 0.6415 1.0000
5.250 1.1800 0.01535 0.00924 -0.1340 0.6319 1.0000
5.500 1.2032 0.01520 0.00910 -0.1330 0.6200 1.0000
5.750 1.2276 0.01508 0.00896 -0.1323 0.6080 1.0000
6.000 1.2514 0.01505 0.00890 -0.1315 0.5943 1.0000
6.250 1.2724 0.01517 0.00900 -0.1302 0.5780 1.0000
6.500 1.2911 0.01538 0.00919 -0.1285 0.5592 1.0000
6.750 1.3092 0.01564 0.00937 -0.1268 0.5395 1.0000
7.000 1.3257 0.01600 0.00961 -0.1247 0.5191 1.0000
7.250 1.3371 0.01650 0.01003 -0.1219 0.4969 1.0000
7.500 1.3455 0.01713 0.01052 -0.1185 0.4744 1.0000
7.750 1.3529 0.01788 0.01115 -0.1152 0.4521 1.0000
8.000 1.3600 0.01872 0.01189 -0.1120 0.4310 1.0000
8.250 1.3672 0.01962 0.01270 -0.1090 0.4114 1.0000
8.500 1.3738 0.02058 0.01359 -0.1060 0.3919 1.0000
8.750 1.3803 0.02157 0.01456 -0.1032 0.3727 1.0000
9.000 1.3872 0.02262 0.01557 -0.1006 0.3550 1.0000
9.250 1.3939 0.02374 0.01664 -0.0981 0.3395 1.0000
9.750 1.4093 0.02609 0.01892 -0.0937 0.3129 1.0000
10.000 1.4179 0.02727 0.02013 -0.0918 0.2999 1.0000
10.250 1.4257 0.02854 0.02139 -0.0898 0.2878 1.0000
10.500 1.4314 0.02998 0.02278 -0.0878 0.2756 1.0000
10.750 1.4374 0.03144 0.02418 -0.0858 0.2649 1.0000
11.000 1.4450 0.03284 0.02565 -0.0842 0.2522 1.0000
11.250 1.4520 0.03433 0.02721 -0.0826 0.2374 1.0000
11.500 1.4549 0.03619 0.02903 -0.0809 0.2173 1.0000
11.750 1.4578 0.03816 0.03098 -0.0792 0.1954 1.0000
12.000 1.4533 0.04085 0.03347 -0.0772 0.1621 1.0000
12.250 1.4441 0.04401 0.03638 -0.0749 0.1248 1.0000
12.500 1.4193 0.04867 0.04056 -0.0718 0.0639 1.0000
12.750 1.4075 0.05234 0.04409 -0.0696 0.0412 1.0000
13.000 1.4041 0.05531 0.04708 -0.0681 0.0344 1.0000
13.250 1.4028 0.05817 0.05002 -0.0669 0.0314 1.0000
13.500 1.3993 0.06138 0.05334 -0.0658 0.0293 1.0000
13.750 1.3959 0.06469 0.05680 -0.0648 0.0281 1.0000
14.000 1.3929 0.06805 0.06032 -0.0641 0.0274 1.0000
14.250 1.3881 0.07172 0.06416 -0.0636 0.0267 1.0000
14.500 1.3819 0.07571 0.06832 -0.0632 0.0261 1.0000
14.750 1.3746 0.07994 0.07269 -0.0631 0.0256 1.0000
15.000 1.3661 0.08441 0.07731 -0.0631 0.0251 1.0000
15.250 1.3572 0.08904 0.08207 -0.0634 0.0246 1.0000
15.500 1.3481 0.09377 0.08690 -0.0638 0.0241 1.0000
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Polar data table (+)
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