WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 50,000 Max Cl/Cd: 33.45 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb13535sm-il-50000-n5.txt Download as CSV file: xf-wb13535sm-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3807 0.10443 0.09747 -0.0514 1.0000 0.0470
-11.000 -0.3892 0.09900 0.09214 -0.0532 1.0000 0.0469
-10.750 -0.4007 0.09315 0.08639 -0.0551 1.0000 0.0467
-10.500 -0.4173 0.08668 0.08003 -0.0575 1.0000 0.0463
-10.250 -0.4387 0.07993 0.07341 -0.0603 1.0000 0.0457
-10.000 -0.4656 0.07309 0.06663 -0.0632 1.0000 0.0450
-9.750 -0.4951 0.06716 0.06072 -0.0656 1.0000 0.0443
-9.500 -0.5276 0.06271 0.05629 -0.0665 1.0000 0.0437
-9.250 -0.5599 0.05972 0.05331 -0.0647 1.0000 0.0431
-9.000 -0.5859 0.05683 0.05034 -0.0625 1.0000 0.0429
-8.750 -0.6054 0.05416 0.04752 -0.0601 1.0000 0.0428
-8.500 -0.6192 0.05155 0.04472 -0.0577 1.0000 0.0430
-8.250 -0.6276 0.04901 0.04194 -0.0555 1.0000 0.0436
-8.000 -0.6087 0.04546 0.03794 -0.0579 0.9925 0.0450
-7.750 -0.5853 0.04236 0.03426 -0.0603 0.9847 0.0478
-7.500 -0.5625 0.03994 0.03174 -0.0617 0.9769 0.0511
-7.250 -0.5391 0.03791 0.02945 -0.0627 0.9692 0.0546
-7.000 -0.5115 0.03593 0.02711 -0.0641 0.9627 0.0593
-6.750 -0.4905 0.03417 0.02530 -0.0646 0.9542 0.0659
-6.500 -0.4647 0.03241 0.02340 -0.0657 0.9476 0.0762
-6.250 -0.4427 0.03078 0.02185 -0.0661 0.9396 0.0946
-6.000 -0.4142 0.02959 0.02094 -0.0675 0.9335 0.1472
-5.750 -0.3902 0.02953 0.02071 -0.0675 0.9251 0.1954
-5.500 -0.3580 0.03016 0.02122 -0.0688 0.9195 0.2353
-5.250 -0.3382 0.03093 0.02196 -0.0676 0.9107 0.2642
-5.000 -0.3063 0.03087 0.02166 -0.0686 0.9056 0.2828
-4.750 -0.2831 0.03052 0.02108 -0.0681 0.8983 0.2933
-4.500 -0.2532 0.03007 0.02029 -0.0688 0.8927 0.3050
-4.250 -0.2230 0.02971 0.01972 -0.0695 0.8874 0.3154
-4.000 -0.1994 0.02945 0.01930 -0.0691 0.8804 0.3249
-3.750 -0.1659 0.02909 0.01871 -0.0704 0.8760 0.3369
-3.500 -0.1431 0.02891 0.01834 -0.0699 0.8692 0.3475
-3.250 -0.1140 0.02870 0.01803 -0.0703 0.8636 0.3590
-3.000 -0.0783 0.02845 0.01763 -0.0719 0.8599 0.3730
-2.750 -0.0612 0.02845 0.01752 -0.0703 0.8519 0.3844
-2.500 -0.0290 0.02831 0.01727 -0.0713 0.8472 0.3995
-2.250 -0.0019 0.02829 0.01715 -0.0714 0.8416 0.4150
-2.000 0.0222 0.02832 0.01712 -0.0710 0.8351 0.4305
-1.750 0.0567 0.02822 0.01696 -0.0722 0.8310 0.4497
-1.500 0.0763 0.02837 0.01707 -0.0711 0.8236 0.4665
-1.250 0.1060 0.02837 0.01701 -0.0716 0.8182 0.4880
-1.000 0.1427 0.02822 0.01688 -0.0731 0.8146 0.5111
-0.750 0.1571 0.02849 0.01716 -0.0711 0.8056 0.5309
-0.500 0.1920 0.02833 0.01703 -0.0722 0.8010 0.5583
-0.250 0.2125 0.02839 0.01716 -0.0711 0.7918 0.5842
0.000 0.2530 0.02781 0.01668 -0.0725 0.7853 0.6218
0.250 0.2769 0.02752 0.01657 -0.0714 0.7738 0.6613
0.500 0.3098 0.02689 0.01627 -0.0714 0.7640 0.7261
0.750 0.4012 0.02580 0.01554 -0.0823 0.7566 1.0000
1.000 0.4228 0.02601 0.01557 -0.0813 0.7458 1.0000
1.250 0.4617 0.02575 0.01512 -0.0827 0.7394 1.0000
1.500 0.4793 0.02607 0.01534 -0.0811 0.7278 1.0000
1.750 0.5026 0.02626 0.01543 -0.0802 0.7177 1.0000
2.000 0.5369 0.02608 0.01515 -0.0807 0.7101 1.0000
2.250 0.5557 0.02638 0.01541 -0.0791 0.6983 1.0000
2.500 0.5795 0.02650 0.01548 -0.0782 0.6875 1.0000
2.750 0.6144 0.02623 0.01515 -0.0787 0.6792 1.0000
3.000 0.6336 0.02648 0.01540 -0.0770 0.6664 1.0000
3.250 0.6549 0.02664 0.01555 -0.0757 0.6536 1.0000
3.500 0.6780 0.02673 0.01563 -0.0745 0.6408 1.0000
3.750 0.7020 0.02677 0.01569 -0.0734 0.6278 1.0000
4.000 0.7261 0.02680 0.01572 -0.0723 0.6142 1.0000
4.250 0.7490 0.02686 0.01579 -0.0711 0.5997 1.0000
4.500 0.7706 0.02696 0.01593 -0.0697 0.5842 1.0000
4.750 0.7919 0.02711 0.01610 -0.0682 0.5683 1.0000
5.000 0.8132 0.02727 0.01628 -0.0668 0.5519 1.0000
5.250 0.8351 0.02745 0.01648 -0.0655 0.5356 1.0000
5.500 0.8574 0.02764 0.01669 -0.0643 0.5196 1.0000
5.750 0.8800 0.02788 0.01693 -0.0632 0.5042 1.0000
6.000 0.9026 0.02817 0.01722 -0.0621 0.4896 1.0000
6.250 0.9251 0.02853 0.01760 -0.0610 0.4756 1.0000
6.500 0.9476 0.02895 0.01801 -0.0600 0.4626 1.0000
6.750 0.9709 0.02939 0.01846 -0.0592 0.4507 1.0000
7.000 0.9962 0.02979 0.01885 -0.0586 0.4396 1.0000
7.250 1.0159 0.03047 0.01965 -0.0575 0.4284 1.0000
7.500 1.0362 0.03118 0.02044 -0.0564 0.4181 1.0000
7.750 1.0616 0.03174 0.02102 -0.0560 0.4087 1.0000
8.000 1.0808 0.03256 0.02198 -0.0549 0.3994 1.0000
8.250 1.1023 0.03336 0.02291 -0.0541 0.3910 1.0000
8.500 1.1257 0.03410 0.02380 -0.0535 0.3827 1.0000
8.750 1.1389 0.03503 0.02487 -0.0516 0.3720 1.0000
9.000 1.1512 0.03575 0.02565 -0.0494 0.3591 1.0000
9.250 1.1605 0.03646 0.02640 -0.0468 0.3459 1.0000
9.500 1.1700 0.03719 0.02717 -0.0442 0.3333 1.0000
9.750 1.1757 0.03798 0.02798 -0.0414 0.3201 1.0000
10.000 1.1726 0.03924 0.02941 -0.0380 0.3080 1.0000
10.250 1.1746 0.04055 0.03089 -0.0354 0.2978 1.0000
10.500 1.1794 0.04169 0.03215 -0.0331 0.2874 1.0000
10.750 1.1797 0.04306 0.03365 -0.0308 0.2761 1.0000
11.000 1.1734 0.04503 0.03587 -0.0284 0.2642 1.0000
11.250 1.1693 0.04707 0.03811 -0.0266 0.2524 1.0000
11.500 1.1620 0.04944 0.04065 -0.0249 0.2379 1.0000
11.750 1.1522 0.05225 0.04360 -0.0237 0.2197 1.0000
12.000 1.1399 0.05568 0.04718 -0.0231 0.1960 1.0000
12.250 1.1294 0.05922 0.05071 -0.0228 0.1660 1.0000
12.500 1.1174 0.06310 0.05439 -0.0226 0.1275 1.0000
12.750 1.0965 0.06838 0.05925 -0.0231 0.0871 1.0000
13.250 1.0609 0.07979 0.07051 -0.0254 0.0641 1.0000
13.500 1.0460 0.08559 0.07636 -0.0270 0.0592 1.0000
13.750 1.0333 0.09125 0.08210 -0.0287 0.0552 1.0000
14.000 1.0209 0.09701 0.08794 -0.0306 0.0521 1.0000
14.250 1.0107 0.10248 0.09347 -0.0324 0.0500 1.0000
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Polar data table (+)
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