WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb13535sm-il-1000000-n5.txt Download as CSV file: xf-wb13535sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7488 0.08435 0.08172 -0.0557 1.0000 0.0041
-15.250 -0.7653 0.07821 0.07550 -0.0589 1.0000 0.0041
-15.000 -0.7925 0.07087 0.06804 -0.0627 1.0000 0.0040
-14.750 -0.8035 0.06615 0.06325 -0.0651 1.0000 0.0039
-14.500 -0.8236 0.06024 0.05727 -0.0682 1.0000 0.0040
-14.250 -0.8459 0.05421 0.05116 -0.0713 1.0000 0.0040
-14.000 -0.8751 0.04754 0.04437 -0.0747 1.0000 0.0040
-13.750 -0.8950 0.04206 0.03881 -0.0774 1.0000 0.0041
-13.500 -0.9266 0.03497 0.03157 -0.0816 1.0000 0.0040
-13.250 -0.9237 0.02915 0.02557 -0.0906 0.9965 0.0041
-13.000 -0.9177 0.02648 0.02274 -0.0922 0.9837 0.0041
-12.750 -0.8975 0.02468 0.02082 -0.0942 0.9754 0.0041
-12.500 -0.8714 0.02348 0.01953 -0.0960 0.9678 0.0043
-12.250 -0.8408 0.02195 0.01786 -0.0991 0.9615 0.0044
-12.000 -0.8071 0.02093 0.01676 -0.1019 0.9530 0.0046
-11.750 -0.7753 0.01973 0.01542 -0.1045 0.9415 0.0047
-11.500 -0.7477 0.01879 0.01434 -0.1058 0.9280 0.0048
-11.250 -0.7253 0.01803 0.01344 -0.1057 0.9138 0.0049
-11.000 -0.7062 0.01731 0.01258 -0.1049 0.9004 0.0050
-10.750 -0.6861 0.01676 0.01191 -0.1039 0.8882 0.0052
-10.500 -0.6668 0.01616 0.01119 -0.1028 0.8763 0.0053
-10.250 -0.6459 0.01568 0.01061 -0.1019 0.8654 0.0054
-10.000 -0.6258 0.01512 0.00994 -0.1008 0.8543 0.0056
-9.750 -0.6064 0.01449 0.00919 -0.0996 0.8425 0.0058
-9.500 -0.5848 0.01405 0.00865 -0.0986 0.8302 0.0061
-9.250 -0.5628 0.01363 0.00813 -0.0977 0.8180 0.0063
-9.000 -0.5397 0.01328 0.00770 -0.0969 0.8068 0.0066
-8.750 -0.5166 0.01294 0.00726 -0.0962 0.7964 0.0068
-8.500 -0.4931 0.01261 0.00685 -0.0955 0.7862 0.0072
-8.250 -0.4687 0.01233 0.00649 -0.0949 0.7770 0.0076
-8.000 -0.4446 0.01205 0.00612 -0.0942 0.7680 0.0078
-7.750 -0.4211 0.01163 0.00562 -0.0935 0.7591 0.0085
-7.500 -0.3965 0.01135 0.00527 -0.0929 0.7511 0.0091
-7.250 -0.3714 0.01109 0.00495 -0.0924 0.7436 0.0098
-7.000 -0.3461 0.01086 0.00466 -0.0919 0.7371 0.0104
-6.750 -0.3202 0.01065 0.00440 -0.0915 0.7306 0.0110
-6.250 -0.2693 0.01015 0.00380 -0.0906 0.7184 0.0142
-6.000 -0.2433 0.00996 0.00356 -0.0902 0.7122 0.0160
-5.750 -0.2174 0.00974 0.00332 -0.0898 0.7070 0.0196
-5.500 -0.1914 0.00951 0.00309 -0.0894 0.7019 0.0260
-5.250 -0.1658 0.00927 0.00285 -0.0890 0.6961 0.0366
-5.000 -0.1419 0.00881 0.00251 -0.0883 0.6898 0.0733
-4.750 -0.1180 0.00840 0.00225 -0.0877 0.6822 0.1157
-4.500 -0.0921 0.00821 0.00211 -0.0873 0.6752 0.1394
-4.250 -0.0654 0.00809 0.00200 -0.0870 0.6689 0.1524
-4.000 -0.0389 0.00799 0.00191 -0.0867 0.6627 0.1652
-3.750 -0.0119 0.00788 0.00182 -0.0865 0.6563 0.1793
-3.500 0.0148 0.00782 0.00174 -0.0862 0.6497 0.1884
-3.250 0.0421 0.00775 0.00166 -0.0860 0.6436 0.1970
-3.000 0.0691 0.00769 0.00159 -0.0858 0.6371 0.2049
-2.750 0.0963 0.00765 0.00152 -0.0856 0.6319 0.2112
-2.500 0.1237 0.00760 0.00146 -0.0854 0.6263 0.2174
-2.250 0.1506 0.00757 0.00141 -0.0852 0.6199 0.2247
-2.000 0.1779 0.00753 0.00137 -0.0850 0.6132 0.2324
-1.750 0.2047 0.00751 0.00133 -0.0847 0.6049 0.2423
-1.500 0.2317 0.00746 0.00130 -0.0845 0.5975 0.2537
-1.250 0.2586 0.00744 0.00127 -0.0842 0.5905 0.2643
-1.000 0.2858 0.00742 0.00126 -0.0841 0.5847 0.2750
-0.750 0.3129 0.00740 0.00125 -0.0838 0.5777 0.2862
-0.500 0.3397 0.00740 0.00125 -0.0836 0.5698 0.2964
-0.250 0.3663 0.00741 0.00125 -0.0833 0.5601 0.3062
0.000 0.3931 0.00743 0.00126 -0.0830 0.5496 0.3169
0.250 0.4194 0.00745 0.00127 -0.0827 0.5389 0.3265
0.750 0.4713 0.00757 0.00133 -0.0818 0.5083 0.3440
1.000 0.4959 0.00769 0.00138 -0.0812 0.4851 0.3527
1.250 0.5195 0.00787 0.00147 -0.0804 0.4551 0.3641
1.500 0.5422 0.00810 0.00159 -0.0794 0.4202 0.3758
1.750 0.5645 0.00836 0.00173 -0.0783 0.3861 0.3879
2.000 0.5881 0.00854 0.00185 -0.0775 0.3653 0.4007
2.250 0.6122 0.00867 0.00197 -0.0769 0.3503 0.4188
2.500 0.6369 0.00877 0.00207 -0.0763 0.3385 0.4362
2.750 0.6617 0.00886 0.00219 -0.0757 0.3293 0.4551
3.250 0.7106 0.00906 0.00243 -0.0744 0.3107 0.4945
3.500 0.7347 0.00918 0.00256 -0.0737 0.3015 0.5129
3.750 0.7587 0.00927 0.00269 -0.0730 0.2936 0.5379
4.000 0.7826 0.00933 0.00283 -0.0723 0.2879 0.5678
4.250 0.8067 0.00937 0.00295 -0.0716 0.2839 0.5974
4.500 0.8295 0.00942 0.00309 -0.0706 0.2781 0.6347
4.750 0.8469 0.00927 0.00325 -0.0685 0.2701 0.7493
5.250 0.9802 0.00957 0.00392 -0.0864 0.2405 1.0000
5.500 1.0014 0.00980 0.00410 -0.0851 0.2299 1.0000
5.750 1.0219 0.01007 0.00430 -0.0838 0.2159 1.0000
6.000 1.0407 0.01040 0.00454 -0.0821 0.1958 1.0000
6.250 1.0515 0.01110 0.00498 -0.0791 0.1542 1.0000
6.500 1.0525 0.01226 0.00575 -0.0744 0.0888 1.0000
6.750 1.0487 0.01363 0.00677 -0.0688 0.0174 1.0000
7.000 1.0641 0.01396 0.00709 -0.0665 0.0138 1.0000
7.250 1.0806 0.01425 0.00740 -0.0645 0.0125 1.0000
7.500 1.0969 0.01457 0.00775 -0.0624 0.0112 1.0000
7.750 1.1131 0.01494 0.00813 -0.0605 0.0102 1.0000
8.000 1.1285 0.01538 0.00860 -0.0584 0.0091 1.0000
8.250 1.1457 0.01575 0.00900 -0.0568 0.0087 1.0000
8.500 1.1621 0.01618 0.00945 -0.0551 0.0082 1.0000
8.750 1.1786 0.01662 0.00992 -0.0534 0.0077 1.0000
9.000 1.1941 0.01714 0.01045 -0.0517 0.0070 1.0000
9.250 1.2080 0.01777 0.01111 -0.0498 0.0065 1.0000
9.500 1.2241 0.01829 0.01166 -0.0483 0.0062 1.0000
9.750 1.2390 0.01890 0.01231 -0.0468 0.0059 1.0000
10.000 1.2534 0.01957 0.01303 -0.0452 0.0057 1.0000
10.250 1.2679 0.02025 0.01374 -0.0437 0.0054 1.0000
10.500 1.2813 0.02102 0.01456 -0.0422 0.0052 1.0000
10.750 1.2940 0.02186 0.01544 -0.0407 0.0051 1.0000
11.000 1.3060 0.02277 0.01638 -0.0393 0.0047 1.0000
11.250 1.3142 0.02400 0.01767 -0.0375 0.0045 1.0000
11.500 1.3248 0.02509 0.01881 -0.0361 0.0044 1.0000
11.750 1.3371 0.02607 0.01984 -0.0349 0.0043 1.0000
12.000 1.3465 0.02732 0.02117 -0.0336 0.0041 1.0000
12.250 1.3579 0.02843 0.02233 -0.0326 0.0040 1.0000
12.500 1.3662 0.02983 0.02379 -0.0315 0.0039 1.0000
12.750 1.3716 0.03153 0.02556 -0.0302 0.0037 1.0000
13.000 1.3806 0.03294 0.02703 -0.0293 0.0036 1.0000
13.250 1.3833 0.03495 0.02912 -0.0282 0.0036 1.0000
13.500 1.3914 0.03653 0.03075 -0.0275 0.0034 1.0000
13.750 1.3952 0.03856 0.03285 -0.0267 0.0034 1.0000
14.000 1.3982 0.04072 0.03506 -0.0260 0.0032 1.0000
14.250 1.4025 0.04280 0.03722 -0.0254 0.0032 1.0000
14.500 1.3978 0.04593 0.04045 -0.0248 0.0031 1.0000
14.750 1.3973 0.04870 0.04331 -0.0245 0.0031 1.0000
15.000 1.3918 0.05211 0.04682 -0.0243 0.0030 1.0000
15.250 1.3899 0.05524 0.05003 -0.0243 0.0030 1.0000
15.500 1.3831 0.05908 0.05399 -0.0244 0.0029 1.0000
15.750 1.3785 0.06272 0.05773 -0.0248 0.0029 1.0000
16.000 1.3724 0.06669 0.06180 -0.0253 0.0029 1.0000
16.250 1.3653 0.07093 0.06614 -0.0260 0.0029 1.0000
16.500 1.3569 0.07545 0.07076 -0.0269 0.0029 1.0000
16.750 1.3461 0.08042 0.07585 -0.0281 0.0029 1.0000
17.000 1.3360 0.08541 0.08094 -0.0294 0.0029 1.0000
17.250 1.3267 0.09039 0.08602 -0.0308 0.0028 1.0000
17.500 1.3210 0.09481 0.09053 -0.0321 0.0028 1.0000
17.750 1.3058 0.10079 0.09662 -0.0340 0.0028 1.0000
18.000 1.2989 0.10549 0.10142 -0.0355 0.0027 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WB-135/35 13.5% smoothed (wb13535sm-il)