WB-135/35 13.5% smoothed (wb13535sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WB-135/35 13.5% smoothed (wb13535sm-il) Reynolds number: 200,000 Max Cl/Cd: 73.79 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-wb13535sm-il-200000.txt Download as CSV file: xf-wb13535sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5255 0.06691 0.06329 -0.0744 1.0000 0.0358
-10.750 -0.5339 0.06248 0.05889 -0.0744 1.0000 0.0349
-10.500 -0.5598 0.05709 0.05350 -0.0760 1.0000 0.0337
-10.250 -0.5934 0.05417 0.05059 -0.0760 1.0000 0.0339
-10.000 -0.6295 0.05297 0.04943 -0.0705 1.0000 0.0330
-9.750 -0.6580 0.05145 0.04784 -0.0667 0.9991 0.0333
-9.500 -0.6486 0.04479 0.04065 -0.0742 0.9890 0.0331
-9.250 -0.6326 0.03947 0.03478 -0.0785 0.9814 0.0323
-9.000 -0.6137 0.03511 0.02986 -0.0808 0.9732 0.0317
-8.750 -0.5890 0.03180 0.02608 -0.0826 0.9667 0.0315
-8.500 -0.5611 0.02926 0.02319 -0.0840 0.9602 0.0318
-8.250 -0.5263 0.02704 0.02068 -0.0863 0.9568 0.0325
-8.000 -0.4994 0.02543 0.01886 -0.0867 0.9490 0.0337
-7.750 -0.4629 0.02417 0.01734 -0.0887 0.9448 0.0354
-7.500 -0.4278 0.02181 0.01496 -0.0910 0.9422 0.0378
-7.250 -0.4016 0.02061 0.01374 -0.0911 0.9342 0.0400
-7.000 -0.3677 0.01946 0.01250 -0.0926 0.9297 0.0427
-6.750 -0.3368 0.01823 0.01120 -0.0936 0.9246 0.0473
-6.500 -0.3108 0.01735 0.01021 -0.0935 0.9164 0.0539
-6.250 -0.2796 0.01598 0.00887 -0.0944 0.9119 0.0739
-6.000 -0.2599 0.01510 0.00848 -0.0934 0.9021 0.1785
-5.750 -0.2254 0.01506 0.00829 -0.0946 0.8974 0.2051
-5.500 -0.2004 0.01505 0.00819 -0.0940 0.8889 0.2206
-5.250 -0.1699 0.01497 0.00804 -0.0944 0.8831 0.2364
-5.000 -0.1445 0.01499 0.00799 -0.0939 0.8754 0.2509
-4.750 -0.1167 0.01498 0.00792 -0.0937 0.8690 0.2659
-4.500 -0.0895 0.01498 0.00780 -0.0935 0.8628 0.2784
-4.250 -0.0635 0.01478 0.00763 -0.0931 0.8557 0.2871
-4.000 -0.0331 0.01454 0.00729 -0.0934 0.8510 0.2968
-3.750 -0.0096 0.01445 0.00717 -0.0925 0.8431 0.3060
-3.500 0.0187 0.01425 0.00695 -0.0924 0.8380 0.3164
-3.250 0.0449 0.01413 0.00679 -0.0920 0.8319 0.3278
-3.000 0.0710 0.01402 0.00663 -0.0916 0.8256 0.3402
-2.750 0.1006 0.01382 0.00640 -0.0917 0.8209 0.3539
-2.500 0.1238 0.01371 0.00634 -0.0907 0.8123 0.3675
-2.250 0.1532 0.01348 0.00606 -0.0906 0.8058 0.3833
-2.000 0.1767 0.01337 0.00598 -0.0896 0.7966 0.3981
-1.750 0.2058 0.01320 0.00577 -0.0895 0.7907 0.4148
-1.500 0.2293 0.01315 0.00576 -0.0886 0.7824 0.4312
-1.250 0.2577 0.01301 0.00561 -0.0884 0.7763 0.4490
-1.000 0.2816 0.01295 0.00561 -0.0875 0.7680 0.4659
-0.750 0.3095 0.01282 0.00548 -0.0872 0.7616 0.4841
-0.500 0.3339 0.01279 0.00552 -0.0864 0.7544 0.5034
-0.250 0.3606 0.01273 0.00547 -0.0860 0.7483 0.5253
0.000 0.3865 0.01265 0.00546 -0.0854 0.7421 0.5471
0.250 0.4112 0.01257 0.00546 -0.0847 0.7350 0.5724
0.500 0.4386 0.01243 0.00538 -0.0843 0.7293 0.6013
0.750 0.4610 0.01230 0.00544 -0.0832 0.7217 0.6344
1.000 0.4874 0.01204 0.00536 -0.0826 0.7157 0.6824
1.250 0.5380 0.01146 0.00544 -0.0869 0.7073 0.8569
1.500 0.6348 0.01131 0.00525 -0.1013 0.6984 1.0000
1.750 0.6576 0.01139 0.00529 -0.1003 0.6894 1.0000
2.000 0.6823 0.01146 0.00528 -0.0995 0.6814 1.0000
2.250 0.7063 0.01151 0.00528 -0.0986 0.6721 1.0000
2.500 0.7293 0.01157 0.00532 -0.0975 0.6618 1.0000
2.750 0.7535 0.01161 0.00531 -0.0965 0.6515 1.0000
3.000 0.7771 0.01165 0.00529 -0.0955 0.6401 1.0000
3.250 0.7991 0.01171 0.00534 -0.0942 0.6269 1.0000
3.500 0.8213 0.01176 0.00538 -0.0928 0.6125 1.0000
3.750 0.8432 0.01182 0.00538 -0.0914 0.5959 1.0000
4.000 0.8636 0.01190 0.00543 -0.0897 0.5751 1.0000
4.250 0.8832 0.01202 0.00546 -0.0879 0.5507 1.0000
4.500 0.9010 0.01221 0.00555 -0.0857 0.5203 1.0000
4.750 0.9176 0.01252 0.00569 -0.0834 0.4869 1.0000
5.000 0.9338 0.01295 0.00591 -0.0811 0.4580 1.0000
5.250 0.9509 0.01341 0.00621 -0.0791 0.4353 1.0000
5.500 0.9692 0.01389 0.00657 -0.0774 0.4183 1.0000
5.750 0.9886 0.01435 0.00694 -0.0759 0.4046 1.0000
6.000 1.0085 0.01480 0.00734 -0.0745 0.3924 1.0000
6.250 1.0280 0.01526 0.00774 -0.0730 0.3803 1.0000
6.500 1.0465 0.01572 0.00814 -0.0714 0.3675 1.0000
6.750 1.0646 0.01619 0.00854 -0.0697 0.3550 1.0000
7.000 1.0832 0.01657 0.00895 -0.0681 0.3445 1.0000
7.250 1.1027 0.01699 0.00939 -0.0667 0.3358 1.0000
7.500 1.1211 0.01746 0.00982 -0.0652 0.3263 1.0000
7.750 1.1349 0.01778 0.01020 -0.0628 0.3137 1.0000
8.000 1.1509 0.01815 0.01063 -0.0608 0.3039 1.0000
8.250 1.1646 0.01857 0.01105 -0.0584 0.2940 1.0000
8.500 1.1760 0.01892 0.01146 -0.0556 0.2836 1.0000
8.750 1.1840 0.01931 0.01190 -0.0523 0.2690 1.0000
9.000 1.1932 0.01977 0.01238 -0.0493 0.2536 1.0000
9.250 1.2021 0.02030 0.01294 -0.0465 0.2325 1.0000
9.500 1.2070 0.02114 0.01365 -0.0434 0.1966 1.0000
9.750 1.2026 0.02273 0.01487 -0.0396 0.1438 1.0000
10.000 1.1797 0.02587 0.01733 -0.0344 0.0592 1.0000
10.250 1.1762 0.02791 0.01923 -0.0315 0.0394 1.0000
10.500 1.1811 0.02944 0.02082 -0.0295 0.0346 1.0000
10.750 1.1840 0.03118 0.02263 -0.0275 0.0312 1.0000
11.000 1.1859 0.03306 0.02462 -0.0256 0.0294 1.0000
11.250 1.1896 0.03487 0.02657 -0.0241 0.0282 1.0000
11.500 1.1916 0.03688 0.02873 -0.0226 0.0275 1.0000
11.750 1.1915 0.03915 0.03113 -0.0213 0.0267 1.0000
12.000 1.1905 0.04158 0.03369 -0.0202 0.0263 1.0000
12.250 1.1865 0.04441 0.03663 -0.0192 0.0257 1.0000
12.500 1.1820 0.04738 0.03971 -0.0184 0.0253 1.0000
12.750 1.1790 0.05031 0.04274 -0.0178 0.0251 1.0000
13.000 1.1747 0.05346 0.04599 -0.0173 0.0249 1.0000
13.250 1.1702 0.05673 0.04933 -0.0169 0.0245 1.0000
13.500 1.1665 0.05994 0.05260 -0.0165 0.0241 1.0000
13.750 1.1643 0.06294 0.05565 -0.0158 0.0237 1.0000
14.000 1.1666 0.06529 0.05800 -0.0146 0.0230 1.0000
14.250 1.1720 0.06760 0.06041 -0.0143 0.0227 1.0000
14.500 1.1789 0.06970 0.06260 -0.0136 0.0224 1.0000
14.750 1.1866 0.07174 0.06472 -0.0129 0.0221 1.0000
15.000 1.1968 0.07349 0.06656 -0.0119 0.0219 1.0000
15.250 1.2070 0.07538 0.06855 -0.0110 0.0218 1.0000
15.500 1.2166 0.07746 0.07076 -0.0100 0.0217 1.0000
15.750 1.2241 0.07991 0.07336 -0.0094 0.0218 1.0000
16.000 1.2298 0.08271 0.07635 -0.0089 0.0219 1.0000
16.250 1.2329 0.08591 0.07972 -0.0087 0.0221 1.0000
16.500 1.2335 0.08955 0.08354 -0.0088 0.0223 1.0000
16.750 1.2325 0.09354 0.08771 -0.0091 0.0226 1.0000
17.000 1.2312 0.09796 0.09231 -0.0093 0.0229 1.0000
17.250 1.2323 0.10206 0.09658 -0.0097 0.0232 1.0000
17.500 1.2232 0.10610 0.10078 -0.0118 0.0235 1.0000
17.750 1.2091 0.11158 0.10647 -0.0145 0.0237 1.0000
18.000 1.1941 0.11764 0.11272 -0.0175 0.0237 1.0000
18.250 1.1724 0.12516 0.12054 -0.0222 0.0243 1.0000
18.500 1.1269 0.13840 0.13421 -0.0312 0.0253 1.0000
18.750 1.0918 0.15066 0.14675 -0.0393 0.0262 1.0000
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Polar data table (+)
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