BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 100,000 Max Cl/Cd: 59.21 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50sm-il-100000-n5.txt Download as CSV file: xf-be50sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BE50 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3575 0.09328 0.08843 -0.0230 1.0000 0.0481
-7.250 -0.3597 0.09100 0.08624 -0.0237 1.0000 0.0503
-7.000 -0.3611 0.08876 0.08410 -0.0294 1.0000 0.0524
-6.750 -0.3552 0.08558 0.08098 -0.0351 1.0000 0.0529
-6.500 -0.3465 0.08187 0.07729 -0.0394 1.0000 0.0530
-6.250 -0.3368 0.07790 0.07333 -0.0425 1.0000 0.0531
-6.000 -0.3267 0.07387 0.06929 -0.0446 1.0000 0.0531
-5.500 -0.3084 0.06075 0.05612 -0.0468 1.0000 0.0298
-5.250 -0.2945 0.05678 0.05211 -0.0491 1.0000 0.0292
-5.000 -0.2745 0.05207 0.04730 -0.0530 1.0000 0.0287
-4.750 -0.2483 0.04651 0.04155 -0.0583 1.0000 0.0283
-4.500 -0.2160 0.04033 0.03499 -0.0642 1.0000 0.0280
-4.250 -0.1711 0.03348 0.02747 -0.0718 0.9983 0.0283
-4.000 -0.1247 0.02825 0.02135 -0.0779 0.9959 0.0310
-3.750 -0.0853 0.02575 0.01844 -0.0814 0.9926 0.0330
-3.500 -0.0454 0.02331 0.01548 -0.0843 0.9891 0.0349
-3.250 -0.0055 0.02149 0.01315 -0.0869 0.9855 0.0388
-3.000 0.0337 0.01998 0.01134 -0.0894 0.9821 0.0435
-2.750 0.0701 0.01888 0.01007 -0.0911 0.9766 0.0480
-2.500 0.1089 0.01799 0.00906 -0.0934 0.9719 0.0565
-2.250 0.1464 0.01721 0.00817 -0.0953 0.9663 0.0651
-2.000 0.1841 0.01659 0.00753 -0.0974 0.9597 0.0813
-1.750 0.2242 0.01596 0.00694 -0.0999 0.9524 0.1070
-1.500 0.2657 0.01528 0.00643 -0.1026 0.9433 0.1541
-1.250 0.3021 0.01461 0.00604 -0.1042 0.9314 0.2391
-1.000 0.3367 0.01397 0.00588 -0.1055 0.9199 0.3963
-0.750 0.3694 0.01347 0.00571 -0.1061 0.9088 0.5300
-0.500 0.3955 0.01259 0.00548 -0.1049 0.8974 0.7329
-0.250 0.4242 0.01219 0.00516 -0.1042 0.8825 1.0000
0.000 0.4554 0.01216 0.00495 -0.1044 0.8677 1.0000
0.250 0.4858 0.01215 0.00478 -0.1045 0.8517 1.0000
0.500 0.5158 0.01214 0.00463 -0.1045 0.8347 1.0000
0.750 0.5456 0.01214 0.00450 -0.1043 0.8168 1.0000
1.000 0.5743 0.01217 0.00440 -0.1040 0.7970 1.0000
1.250 0.6027 0.01222 0.00433 -0.1036 0.7756 1.0000
1.500 0.6307 0.01230 0.00429 -0.1031 0.7524 1.0000
1.750 0.6584 0.01241 0.00426 -0.1026 0.7281 1.0000
2.000 0.6855 0.01255 0.00429 -0.1020 0.7015 1.0000
2.250 0.7121 0.01274 0.00434 -0.1014 0.6734 1.0000
2.500 0.7384 0.01296 0.00442 -0.1007 0.6436 1.0000
2.750 0.7644 0.01322 0.00454 -0.1000 0.6126 1.0000
3.000 0.7900 0.01352 0.00472 -0.0993 0.5806 1.0000
3.250 0.8154 0.01385 0.00491 -0.0986 0.5487 1.0000
3.500 0.8405 0.01422 0.00513 -0.0979 0.5177 1.0000
3.750 0.8655 0.01462 0.00540 -0.0972 0.4883 1.0000
4.000 0.8905 0.01504 0.00570 -0.0965 0.4615 1.0000
4.250 0.9154 0.01548 0.00609 -0.0959 0.4375 1.0000
4.500 0.9402 0.01594 0.00646 -0.0953 0.4168 1.0000
4.750 0.9652 0.01640 0.00688 -0.0948 0.3977 1.0000
5.000 0.9901 0.01687 0.00733 -0.0942 0.3807 1.0000
5.250 1.0149 0.01735 0.00785 -0.0937 0.3649 1.0000
5.500 1.0397 0.01785 0.00836 -0.0931 0.3504 1.0000
5.750 1.0644 0.01835 0.00890 -0.0926 0.3364 1.0000
6.000 1.0890 0.01886 0.00947 -0.0920 0.3231 1.0000
6.250 1.1133 0.01939 0.01010 -0.0914 0.3099 1.0000
6.500 1.1374 0.01992 0.01073 -0.0908 0.2969 1.0000
6.750 1.1612 0.02047 0.01137 -0.0901 0.2835 1.0000
7.000 1.1843 0.02099 0.01200 -0.0893 0.2671 1.0000
7.250 1.2058 0.02149 0.01253 -0.0884 0.2426 1.0000
7.500 1.2268 0.02204 0.01313 -0.0875 0.2119 1.0000
7.750 1.2475 0.02272 0.01381 -0.0866 0.1817 1.0000
8.000 1.2667 0.02364 0.01464 -0.0855 0.1430 1.0000
8.250 1.2820 0.02516 0.01586 -0.0841 0.0911 1.0000
8.500 1.2940 0.02717 0.01759 -0.0822 0.0562 1.0000
8.750 1.3067 0.02898 0.01943 -0.0803 0.0442 1.0000
9.000 1.3175 0.03083 0.02135 -0.0781 0.0378 1.0000
9.250 1.3293 0.03240 0.02316 -0.0761 0.0329 1.0000
9.500 1.3354 0.03441 0.02528 -0.0736 0.0299 1.0000
9.750 1.3418 0.03625 0.02733 -0.0710 0.0283 1.0000
10.000 1.3467 0.03809 0.02939 -0.0682 0.0269 1.0000
10.250 1.3491 0.04002 0.03149 -0.0653 0.0257 1.0000
10.500 1.3513 0.04204 0.03367 -0.0627 0.0243 1.0000
10.750 1.3522 0.04421 0.03596 -0.0604 0.0230 1.0000
11.000 1.3499 0.04685 0.03869 -0.0582 0.0218 1.0000
11.250 1.3496 0.04964 0.04162 -0.0563 0.0208 1.0000
11.500 1.3514 0.05233 0.04455 -0.0546 0.0203 1.0000
11.750 1.3518 0.05531 0.04777 -0.0532 0.0197 1.0000
12.000 1.3505 0.05857 0.05132 -0.0520 0.0193 1.0000
12.250 1.3473 0.06213 0.05514 -0.0512 0.0189 1.0000
12.500 1.3417 0.06608 0.05935 -0.0508 0.0186 1.0000
12.750 1.3339 0.07040 0.06392 -0.0509 0.0183 1.0000
13.000 1.3241 0.07514 0.06891 -0.0517 0.0180 1.0000
13.250 1.3124 0.08035 0.07437 -0.0531 0.0178 1.0000
13.500 1.2991 0.08608 0.08032 -0.0553 0.0176 1.0000
13.750 1.2841 0.09238 0.08686 -0.0582 0.0175 1.0000
14.000 1.2676 0.09936 0.09406 -0.0618 0.0175 1.0000
14.250 1.2494 0.10710 0.10203 -0.0662 0.0176 1.0000
14.500 1.2296 0.11578 0.11092 -0.0715 0.0178 1.0000
14.750 1.2085 0.12545 0.12079 -0.0777 0.0181 1.0000
15.000 1.1863 0.13610 0.13160 -0.0847 0.0185 1.0000
15.250 1.1634 0.14784 0.14343 -0.0923 0.0190 1.0000
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Polar data table (+)
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