WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 500,000 Max Cl/Cd: 84.6 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-wb13535sm-il-500000-n5.txt Download as CSV file: xf-wb13535sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.5292 0.11752 0.11503 -0.0400 1.0000 0.0064
-14.750 -0.6222 0.09371 0.09082 -0.0516 1.0000 0.0058
-14.500 -0.6397 0.08666 0.08367 -0.0552 1.0000 0.0058
-14.250 -0.6501 0.08115 0.07811 -0.0581 1.0000 0.0060
-14.000 -0.6650 0.07512 0.07199 -0.0613 1.0000 0.0060
-13.750 -0.6787 0.06970 0.06650 -0.0642 1.0000 0.0060
-13.500 -0.6978 0.06374 0.06043 -0.0672 1.0000 0.0060
-13.250 -0.7098 0.05895 0.05557 -0.0697 1.0000 0.0060
-13.000 -0.7312 0.05320 0.04968 -0.0724 1.0000 0.0059
-12.750 -0.7431 0.04879 0.04520 -0.0745 1.0000 0.0059
-12.500 -0.7528 0.04473 0.04110 -0.0765 1.0000 0.0061
-12.250 -0.7722 0.03993 0.03617 -0.0784 1.0000 0.0060
-12.000 -0.7756 0.03587 0.03202 -0.0823 0.9988 0.0061
-11.500 -0.7509 0.02887 0.02462 -0.0923 0.9743 0.0063
-11.250 -0.7299 0.02697 0.02255 -0.0945 0.9652 0.0064
-11.000 -0.7059 0.02512 0.02052 -0.0967 0.9568 0.0066
-10.500 -0.6510 0.02218 0.01726 -0.1008 0.9390 0.0071
-10.250 -0.6236 0.02105 0.01597 -0.1022 0.9292 0.0074
-10.000 -0.5963 0.02016 0.01491 -0.1031 0.9187 0.0077
-9.750 -0.5766 0.01904 0.01363 -0.1028 0.9062 0.0080
-9.500 -0.5567 0.01819 0.01267 -0.1021 0.8941 0.0084
-9.250 -0.5361 0.01747 0.01184 -0.1013 0.8830 0.0087
-9.000 -0.5146 0.01687 0.01113 -0.1006 0.8724 0.0091
-8.750 -0.4936 0.01627 0.01041 -0.0997 0.8614 0.0094
-8.500 -0.4723 0.01569 0.00970 -0.0987 0.8503 0.0099
-8.250 -0.4504 0.01517 0.00905 -0.0978 0.8395 0.0104
-8.000 -0.4278 0.01470 0.00844 -0.0970 0.8289 0.0108
-7.750 -0.4064 0.01408 0.00769 -0.0960 0.8183 0.0115
-7.500 -0.3834 0.01362 0.00714 -0.0952 0.8088 0.0126
-7.000 -0.3354 0.01290 0.00622 -0.0939 0.7904 0.0147
-6.750 -0.3111 0.01256 0.00577 -0.0932 0.7819 0.0158
-6.500 -0.2870 0.01217 0.00530 -0.0926 0.7733 0.0181
-6.250 -0.2620 0.01189 0.00493 -0.0920 0.7660 0.0210
-6.000 -0.2373 0.01156 0.00455 -0.0915 0.7587 0.0267
-5.750 -0.2124 0.01124 0.00419 -0.0909 0.7523 0.0358
-5.500 -0.1895 0.01065 0.00373 -0.0902 0.7455 0.0723
-5.250 -0.1663 0.01015 0.00341 -0.0895 0.7393 0.1223
-5.000 -0.1404 0.00992 0.00324 -0.0892 0.7331 0.1467
-4.750 -0.1141 0.00978 0.00309 -0.0888 0.7274 0.1628
-4.500 -0.0875 0.00966 0.00296 -0.0886 0.7224 0.1760
-4.250 -0.0609 0.00953 0.00284 -0.0883 0.7164 0.1910
-4.000 -0.0345 0.00945 0.00272 -0.0879 0.7099 0.2020
-3.750 -0.0079 0.00936 0.00260 -0.0876 0.7023 0.2114
-3.500 0.0184 0.00929 0.00248 -0.0872 0.6947 0.2184
-3.250 0.0453 0.00922 0.00238 -0.0870 0.6876 0.2262
-3.000 0.0718 0.00915 0.00228 -0.0866 0.6811 0.2335
-2.750 0.0988 0.00910 0.00219 -0.0864 0.6752 0.2418
-2.500 0.1255 0.00903 0.00212 -0.0861 0.6687 0.2509
-2.250 0.1521 0.00899 0.00206 -0.0858 0.6624 0.2617
-1.750 0.2058 0.00891 0.00196 -0.0852 0.6501 0.2848
-1.500 0.2327 0.00886 0.00193 -0.0850 0.6440 0.2956
-1.250 0.2594 0.00884 0.00189 -0.0847 0.6371 0.3058
-1.000 0.2861 0.00883 0.00187 -0.0844 0.6297 0.3173
-0.750 0.3126 0.00880 0.00185 -0.0841 0.6221 0.3287
-0.500 0.3393 0.00879 0.00183 -0.0838 0.6161 0.3392
-0.250 0.3662 0.00878 0.00183 -0.0835 0.6096 0.3495
0.000 0.3925 0.00877 0.00183 -0.0832 0.6034 0.3601
0.250 0.4193 0.00875 0.00184 -0.0829 0.5963 0.3716
0.500 0.4452 0.00876 0.00186 -0.0825 0.5884 0.3850
0.750 0.4715 0.00875 0.00188 -0.0821 0.5793 0.3992
1.000 0.4973 0.00877 0.00191 -0.0817 0.5694 0.4133
1.250 0.5226 0.00879 0.00196 -0.0811 0.5585 0.4301
1.500 0.5480 0.00881 0.00201 -0.0806 0.5462 0.4489
1.750 0.5729 0.00886 0.00207 -0.0800 0.5316 0.4673
2.000 0.5969 0.00893 0.00214 -0.0792 0.5134 0.4874
2.250 0.6199 0.00905 0.00223 -0.0782 0.4886 0.5069
2.500 0.6405 0.00928 0.00236 -0.0768 0.4548 0.5271
2.750 0.6606 0.00954 0.00253 -0.0754 0.4203 0.5484
3.000 0.6808 0.00978 0.00272 -0.0740 0.3928 0.5744
3.250 0.7017 0.00994 0.00290 -0.0727 0.3737 0.6083
3.500 0.7219 0.01000 0.00308 -0.0712 0.3596 0.6588
4.000 0.8458 0.01013 0.00380 -0.0867 0.3254 1.0000
4.250 0.8675 0.01035 0.00398 -0.0856 0.3167 1.0000
4.500 0.8893 0.01057 0.00416 -0.0844 0.3089 1.0000
4.750 0.9111 0.01078 0.00436 -0.0833 0.3027 1.0000
5.000 0.9323 0.01102 0.00456 -0.0821 0.2933 1.0000
5.250 0.9530 0.01127 0.00477 -0.0807 0.2818 1.0000
5.500 0.9735 0.01153 0.00500 -0.0794 0.2738 1.0000
5.750 0.9946 0.01176 0.00521 -0.0781 0.2650 1.0000
6.000 1.0148 0.01202 0.00545 -0.0768 0.2560 1.0000
6.250 1.0339 0.01231 0.00569 -0.0752 0.2449 1.0000
6.500 1.0530 0.01261 0.00595 -0.0737 0.2315 1.0000
6.750 1.0709 0.01294 0.00623 -0.0719 0.2154 1.0000
7.000 1.0833 0.01350 0.00661 -0.0693 0.1836 1.0000
7.250 1.0831 0.01446 0.00726 -0.0644 0.1355 1.0000
7.500 1.0627 0.01653 0.00873 -0.0567 0.0366 1.0000
7.750 1.0722 0.01732 0.00945 -0.0539 0.0175 1.0000
8.000 1.0868 0.01787 0.01004 -0.0519 0.0150 1.0000
8.250 1.1012 0.01847 0.01069 -0.0499 0.0130 1.0000
8.500 1.1167 0.01901 0.01129 -0.0483 0.0123 1.0000
8.750 1.1315 0.01961 0.01195 -0.0466 0.0114 1.0000
9.000 1.1451 0.02030 0.01270 -0.0448 0.0104 1.0000
9.250 1.1578 0.02109 0.01355 -0.0430 0.0099 1.0000
9.500 1.1673 0.02211 0.01465 -0.0409 0.0092 1.0000
9.750 1.1796 0.02298 0.01558 -0.0393 0.0088 1.0000
10.000 1.1915 0.02390 0.01657 -0.0377 0.0085 1.0000
10.250 1.2036 0.02483 0.01755 -0.0363 0.0079 1.0000
10.500 1.2137 0.02594 0.01875 -0.0348 0.0076 1.0000
10.750 1.2228 0.02716 0.02004 -0.0333 0.0074 1.0000
11.000 1.2318 0.02843 0.02136 -0.0319 0.0070 1.0000
11.250 1.2374 0.03003 0.02303 -0.0304 0.0067 1.0000
11.500 1.2407 0.03186 0.02495 -0.0290 0.0066 1.0000
11.750 1.2424 0.03392 0.02709 -0.0276 0.0064 1.0000
12.000 1.2482 0.03567 0.02894 -0.0266 0.0061 1.0000
12.250 1.2504 0.03781 0.03118 -0.0256 0.0061 1.0000
12.500 1.2527 0.04002 0.03348 -0.0247 0.0060 1.0000
12.750 1.2546 0.04232 0.03587 -0.0240 0.0057 1.0000
13.000 1.2529 0.04507 0.03874 -0.0233 0.0057 1.0000
13.250 1.2512 0.04794 0.04170 -0.0228 0.0056 1.0000
13.500 1.2509 0.05073 0.04459 -0.0225 0.0054 1.0000
13.750 1.2490 0.05380 0.04775 -0.0224 0.0054 1.0000
14.000 1.2479 0.05689 0.05092 -0.0224 0.0052 1.0000
14.250 1.2494 0.05972 0.05384 -0.0225 0.0050 1.0000
14.500 1.2450 0.06337 0.05758 -0.0228 0.0049 1.0000
14.750 1.2398 0.06723 0.06154 -0.0233 0.0049 1.0000
15.000 1.2396 0.07057 0.06494 -0.0239 0.0047 1.0000
15.250 1.2356 0.07447 0.06893 -0.0247 0.0047 1.0000
15.500 1.2264 0.07912 0.07367 -0.0256 0.0046 1.0000
15.750 1.2208 0.08337 0.07801 -0.0265 0.0046 1.0000
16.000 1.2123 0.08801 0.08273 -0.0276 0.0045 1.0000
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Polar data table (+)
Polar graphs
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