WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.23 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb13535sm-il-1000000.txt Download as CSV file: xf-wb13535sm-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6966 0.08469 0.08234 -0.0560 1.0000 0.0078
-14.750 -0.7114 0.07840 0.07598 -0.0595 1.0000 0.0079
-14.500 -0.7442 0.06973 0.06713 -0.0644 1.0000 0.0077
-14.250 -0.7267 0.06882 0.06632 -0.0653 1.0000 0.0081
-14.000 -0.7662 0.05999 0.05726 -0.0700 1.0000 0.0079
-13.750 -0.7828 0.05458 0.05174 -0.0730 1.0000 0.0078
-13.500 -0.7946 0.04988 0.04696 -0.0757 1.0000 0.0079
-13.250 -0.8064 0.04530 0.04229 -0.0782 1.0000 0.0079
-13.000 -0.8141 0.04128 0.03821 -0.0807 1.0000 0.0081
-12.750 -0.8326 0.03622 0.03301 -0.0834 1.0000 0.0080
-12.500 -0.8402 0.03269 0.02940 -0.0862 1.0000 0.0080
-12.250 -0.8579 0.03020 0.02678 -0.0848 0.9990 0.0081
-12.000 -0.8354 0.02803 0.02447 -0.0881 0.9944 0.0082
-11.750 -0.8130 0.02623 0.02254 -0.0901 0.9892 0.0084
-11.500 -0.7883 0.02454 0.02072 -0.0922 0.9849 0.0086
-11.250 -0.7640 0.02323 0.01930 -0.0934 0.9796 0.0088
-11.000 -0.7394 0.02190 0.01785 -0.0945 0.9737 0.0091
-10.750 -0.7091 0.02065 0.01647 -0.0965 0.9704 0.0093
-10.500 -0.6825 0.01938 0.01508 -0.0977 0.9629 0.0094
-10.250 -0.6479 0.01866 0.01426 -0.0999 0.9577 0.0097
-10.000 -0.6177 0.01772 0.01321 -0.1013 0.9488 0.0098
-9.750 -0.5974 0.01590 0.01120 -0.1015 0.9358 0.0104
-9.500 -0.5727 0.01516 0.01038 -0.1015 0.9241 0.0108
-9.250 -0.5497 0.01459 0.00970 -0.1009 0.9123 0.0111
-9.000 -0.5275 0.01413 0.00915 -0.1001 0.9008 0.0116
-8.750 -0.5049 0.01370 0.00863 -0.0992 0.8899 0.0121
-8.500 -0.4819 0.01332 0.00815 -0.0984 0.8791 0.0126
-8.250 -0.4581 0.01304 0.00779 -0.0977 0.8678 0.0129
-8.000 -0.4396 0.01223 0.00684 -0.0961 0.8559 0.0138
-7.750 -0.4171 0.01178 0.00629 -0.0952 0.8449 0.0145
-7.500 -0.3934 0.01146 0.00589 -0.0944 0.8341 0.0153
-7.250 -0.3692 0.01117 0.00552 -0.0937 0.8229 0.0162
-7.000 -0.3445 0.01091 0.00518 -0.0930 0.8122 0.0168
-6.750 -0.3214 0.01047 0.00463 -0.0921 0.8018 0.0183
-6.500 -0.2969 0.01020 0.00429 -0.0914 0.7919 0.0200
-6.250 -0.2712 0.01001 0.00404 -0.0910 0.7829 0.0217
-6.000 -0.2469 0.00967 0.00364 -0.0902 0.7746 0.0259
-5.750 -0.2219 0.00936 0.00331 -0.0896 0.7664 0.0331
-5.500 -0.2008 0.00864 0.00279 -0.0885 0.7588 0.0858
-5.250 -0.1773 0.00817 0.00254 -0.0878 0.7513 0.1371
-5.000 -0.1513 0.00803 0.00241 -0.0874 0.7441 0.1557
-4.750 -0.1246 0.00792 0.00230 -0.0871 0.7364 0.1679
-4.500 -0.0981 0.00785 0.00219 -0.0868 0.7288 0.1788
-4.250 -0.0710 0.00777 0.00210 -0.0865 0.7213 0.1882
-4.000 -0.0447 0.00769 0.00201 -0.0862 0.7142 0.1984
-3.750 -0.0175 0.00761 0.00192 -0.0859 0.7076 0.2079
-3.250 0.0363 0.00746 0.00178 -0.0854 0.6957 0.2319
-3.000 0.0633 0.00738 0.00170 -0.0852 0.6898 0.2422
-2.750 0.0902 0.00734 0.00164 -0.0849 0.6840 0.2522
-2.250 0.1445 0.00722 0.00153 -0.0844 0.6723 0.2775
-2.000 0.1716 0.00717 0.00150 -0.0842 0.6668 0.2907
-1.750 0.1989 0.00712 0.00147 -0.0840 0.6608 0.3029
-1.500 0.2258 0.00711 0.00144 -0.0837 0.6550 0.3142
-1.250 0.2534 0.00707 0.00142 -0.0836 0.6497 0.3249
-1.000 0.2805 0.00704 0.00140 -0.0834 0.6439 0.3368
-0.750 0.3074 0.00703 0.00139 -0.0831 0.6387 0.3481
-0.500 0.3350 0.00699 0.00138 -0.0830 0.6334 0.3592
-0.250 0.3621 0.00698 0.00137 -0.0827 0.6278 0.3705
0.000 0.3890 0.00696 0.00138 -0.0825 0.6224 0.3830
0.250 0.4162 0.00693 0.00138 -0.0823 0.6163 0.3963
0.500 0.4426 0.00693 0.00140 -0.0819 0.6097 0.4124
0.750 0.4696 0.00689 0.00142 -0.0817 0.6026 0.4298
1.000 0.4958 0.00690 0.00144 -0.0813 0.5948 0.4475
1.250 0.5226 0.00688 0.00147 -0.0810 0.5870 0.4666
1.500 0.5484 0.00689 0.00151 -0.0806 0.5783 0.4875
1.750 0.5747 0.00689 0.00155 -0.0802 0.5681 0.5093
2.000 0.6004 0.00690 0.00160 -0.0797 0.5567 0.5304
2.250 0.6255 0.00694 0.00166 -0.0791 0.5420 0.5528
2.500 0.6494 0.00700 0.00173 -0.0783 0.5222 0.5779
2.750 0.6721 0.00711 0.00181 -0.0772 0.4945 0.6057
3.000 0.6918 0.00728 0.00195 -0.0756 0.4575 0.6472
3.250 0.7060 0.00737 0.00215 -0.0729 0.4148 0.7433
3.500 0.8164 0.00772 0.00271 -0.0917 0.3551 0.9982
3.750 0.8480 0.00796 0.00287 -0.0927 0.3400 1.0000
4.250 0.8926 0.00837 0.00316 -0.0906 0.3170 1.0000
4.500 0.9149 0.00856 0.00332 -0.0895 0.3080 1.0000
4.750 0.9375 0.00875 0.00347 -0.0884 0.3002 1.0000
5.000 0.9600 0.00893 0.00362 -0.0874 0.2918 1.0000
5.250 0.9820 0.00913 0.00379 -0.0863 0.2839 1.0000
5.500 1.0046 0.00930 0.00395 -0.0852 0.2769 1.0000
5.750 1.0265 0.00950 0.00412 -0.0841 0.2694 1.0000
6.000 1.0487 0.00969 0.00429 -0.0830 0.2611 1.0000
6.250 1.0693 0.00994 0.00450 -0.0817 0.2507 1.0000
6.500 1.0904 0.01016 0.00468 -0.0804 0.2390 1.0000
6.750 1.1089 0.01050 0.00491 -0.0787 0.2168 1.0000
7.000 1.1191 0.01121 0.00534 -0.0756 0.1715 1.0000
7.250 1.1121 0.01271 0.00632 -0.0695 0.0907 1.0000
7.500 1.0985 0.01426 0.00747 -0.0622 0.0203 1.0000
7.750 1.1126 0.01470 0.00793 -0.0597 0.0163 1.0000
8.000 1.1276 0.01513 0.00839 -0.0576 0.0151 1.0000
8.250 1.1414 0.01567 0.00897 -0.0552 0.0136 1.0000
8.500 1.1575 0.01611 0.00945 -0.0534 0.0132 1.0000
8.750 1.1728 0.01662 0.01000 -0.0515 0.0126 1.0000
9.000 1.1874 0.01718 0.01061 -0.0496 0.0121 1.0000
9.250 1.2012 0.01781 0.01128 -0.0477 0.0116 1.0000
9.500 1.2127 0.01861 0.01212 -0.0456 0.0109 1.0000
9.750 1.2217 0.01959 0.01318 -0.0432 0.0105 1.0000
10.000 1.2290 0.02072 0.01440 -0.0408 0.0101 1.0000
10.250 1.2448 0.02134 0.01505 -0.0396 0.0098 1.0000
10.500 1.2558 0.02230 0.01607 -0.0379 0.0096 1.0000
10.750 1.2665 0.02331 0.01713 -0.0363 0.0092 1.0000
11.000 1.2769 0.02438 0.01825 -0.0347 0.0089 1.0000
11.250 1.2837 0.02576 0.01971 -0.0330 0.0087 1.0000
11.500 1.2927 0.02702 0.02102 -0.0317 0.0085 1.0000
11.750 1.2979 0.02863 0.02268 -0.0302 0.0082 1.0000
12.000 1.3032 0.03028 0.02440 -0.0288 0.0080 1.0000
12.250 1.3031 0.03247 0.02668 -0.0274 0.0079 1.0000
12.500 1.2941 0.03554 0.02985 -0.0257 0.0076 1.0000
12.750 1.2958 0.03775 0.03213 -0.0247 0.0076 1.0000
13.000 1.2818 0.04153 0.03602 -0.0234 0.0075 1.0000
13.250 1.2962 0.04269 0.03724 -0.0231 0.0073 1.0000
13.500 1.2979 0.04512 0.03974 -0.0226 0.0072 1.0000
13.750 1.2937 0.04824 0.04295 -0.0220 0.0072 1.0000
14.000 1.3012 0.05025 0.04503 -0.0219 0.0069 1.0000
14.250 1.3037 0.05279 0.04764 -0.0218 0.0068 1.0000
14.500 1.2995 0.05615 0.05108 -0.0216 0.0067 1.0000
14.750 1.2993 0.05917 0.05418 -0.0217 0.0065 1.0000
15.000 1.2999 0.06217 0.05726 -0.0219 0.0064 1.0000
15.250 1.2971 0.06559 0.06076 -0.0221 0.0063 1.0000
15.500 1.2937 0.06920 0.06445 -0.0225 0.0062 1.0000
15.750 1.2927 0.07262 0.06794 -0.0231 0.0061 1.0000
16.000 1.2894 0.07632 0.07172 -0.0237 0.0060 1.0000
16.250 1.2858 0.08004 0.07551 -0.0242 0.0060 1.0000
16.500 1.2840 0.08375 0.07930 -0.0251 0.0059 1.0000
16.750 1.2812 0.08750 0.08312 -0.0259 0.0059 1.0000
17.000 1.2782 0.09145 0.08712 -0.0270 0.0057 1.0000
17.250 1.2750 0.09526 0.09101 -0.0278 0.0057 1.0000
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Polar data table (+)
Polar graphs
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