BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 200,000 Max Cl/Cd: 81.22 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50sm-il-200000.txt Download as CSV file: xf-be50sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3577 0.09125 0.08784 -0.0239 1.0000 0.0391
-7.250 -0.3624 0.08937 0.08604 -0.0259 1.0000 0.0399
-7.000 -0.3599 0.08687 0.08361 -0.0304 1.0000 0.0404
-6.750 -0.3545 0.08384 0.08061 -0.0341 1.0000 0.0407
-6.500 -0.3473 0.08050 0.07729 -0.0372 1.0000 0.0408
-6.250 -0.3499 0.07512 0.07197 -0.0371 1.0000 0.0415
-6.000 -0.3494 0.07247 0.06936 -0.0337 1.0000 0.0423
-5.750 -0.3452 0.07017 0.06709 -0.0320 1.0000 0.0432
-5.500 -0.3384 0.06763 0.06457 -0.0320 1.0000 0.0444
-5.250 -0.3284 0.06468 0.06160 -0.0336 1.0000 0.0461
-5.000 -0.3129 0.06106 0.05796 -0.0372 1.0000 0.0487
-4.750 -0.2624 0.05158 0.04807 -0.0552 1.0000 0.0539
-4.500 -0.2599 0.05029 0.04695 -0.0513 1.0000 0.0556
-4.250 -0.2334 0.04777 0.04440 -0.0536 0.9981 0.0594
-4.000 -0.1706 0.03980 0.03588 -0.0675 0.9954 0.0682
-3.750 -0.1341 0.03701 0.03307 -0.0711 0.9921 0.0718
-3.500 -0.0838 0.03226 0.02779 -0.0784 0.9888 0.0826
-3.250 -0.0217 0.02142 0.01520 -0.0841 0.9907 0.0404
-3.000 0.0200 0.01890 0.01233 -0.0876 0.9882 0.0454
-2.750 0.0640 0.01721 0.01028 -0.0906 0.9855 0.0485
-2.500 0.1109 0.01580 0.00861 -0.0942 0.9817 0.0556
-2.250 0.1559 0.01478 0.00752 -0.0973 0.9744 0.0637
-2.000 0.2040 0.01386 0.00658 -0.1012 0.9702 0.0785
-1.750 0.2429 0.01304 0.00586 -0.1035 0.9629 0.1007
-1.500 0.2875 0.01226 0.00530 -0.1069 0.9583 0.1569
-1.250 0.3298 0.01133 0.00500 -0.1101 0.9530 0.3139
-1.000 0.3670 0.01064 0.00490 -0.1120 0.9454 0.5114
-0.750 0.3982 0.00977 0.00471 -0.1121 0.9373 0.7090
-0.500 0.4290 0.00912 0.00432 -0.1115 0.9282 1.0000
-0.250 0.4598 0.00901 0.00408 -0.1116 0.9158 1.0000
0.000 0.4896 0.00892 0.00387 -0.1114 0.9028 1.0000
0.250 0.5184 0.00883 0.00368 -0.1110 0.8886 1.0000
0.500 0.5465 0.00877 0.00351 -0.1105 0.8734 1.0000
0.750 0.5741 0.00872 0.00336 -0.1098 0.8571 1.0000
1.000 0.6006 0.00873 0.00328 -0.1090 0.8372 1.0000
1.250 0.6274 0.00875 0.00319 -0.1082 0.8171 1.0000
1.500 0.6539 0.00881 0.00314 -0.1074 0.7947 1.0000
1.750 0.6804 0.00890 0.00310 -0.1066 0.7712 1.0000
2.000 0.7065 0.00903 0.00312 -0.1058 0.7449 1.0000
2.250 0.7325 0.00920 0.00315 -0.1051 0.7166 1.0000
2.500 0.7583 0.00941 0.00321 -0.1043 0.6857 1.0000
2.750 0.7838 0.00965 0.00330 -0.1035 0.6518 1.0000
3.000 0.8089 0.00996 0.00343 -0.1027 0.6159 1.0000
3.250 0.8339 0.01030 0.00359 -0.1019 0.5770 1.0000
3.500 0.8586 0.01068 0.00379 -0.1011 0.5382 1.0000
3.750 0.8832 0.01112 0.00402 -0.1004 0.5023 1.0000
4.000 0.9080 0.01155 0.00432 -0.0998 0.4709 1.0000
4.250 0.9329 0.01201 0.00463 -0.0992 0.4445 1.0000
4.500 0.9581 0.01244 0.00497 -0.0987 0.4215 1.0000
4.750 0.9832 0.01292 0.00533 -0.0982 0.4025 1.0000
5.000 1.0086 0.01335 0.00573 -0.0978 0.3848 1.0000
5.250 1.0339 0.01379 0.00617 -0.0973 0.3686 1.0000
5.500 1.0592 0.01424 0.00660 -0.0968 0.3536 1.0000
5.750 1.0844 0.01469 0.00705 -0.0964 0.3393 1.0000
6.000 1.1094 0.01513 0.00751 -0.0959 0.3255 1.0000
6.250 1.1342 0.01556 0.00800 -0.0954 0.3111 1.0000
6.500 1.1581 0.01588 0.00833 -0.0947 0.2915 1.0000
6.750 1.1817 0.01620 0.00867 -0.0941 0.2706 1.0000
7.000 1.2057 0.01654 0.00906 -0.0935 0.2509 1.0000
7.250 1.2290 0.01694 0.00949 -0.0928 0.2303 1.0000
7.500 1.2524 0.01735 0.00994 -0.0921 0.2061 1.0000
7.750 1.2747 0.01791 0.01047 -0.0914 0.1708 1.0000
8.000 1.2856 0.02011 0.01190 -0.0893 0.0706 1.0000
8.250 1.2983 0.02213 0.01378 -0.0871 0.0459 1.0000
8.500 1.3101 0.02401 0.01570 -0.0847 0.0389 1.0000
8.750 1.3261 0.02531 0.01716 -0.0828 0.0352 1.0000
9.000 1.3389 0.02686 0.01880 -0.0808 0.0315 1.0000
9.250 1.3456 0.02930 0.02129 -0.0779 0.0293 1.0000
9.500 1.3600 0.03086 0.02301 -0.0758 0.0280 1.0000
9.750 1.3735 0.03266 0.02496 -0.0737 0.0265 1.0000
10.000 1.3862 0.03437 0.02680 -0.0718 0.0248 1.0000
10.250 1.3969 0.03617 0.02866 -0.0698 0.0231 1.0000
10.500 1.4078 0.03942 0.03202 -0.0680 0.0218 1.0000
10.750 1.4183 0.04400 0.03689 -0.0662 0.0212 1.0000
11.000 1.4235 0.04632 0.03951 -0.0636 0.0209 1.0000
11.250 1.4236 0.04897 0.04248 -0.0604 0.0208 1.0000
11.500 1.4200 0.05194 0.04575 -0.0573 0.0207 1.0000
11.750 1.4126 0.05522 0.04932 -0.0543 0.0206 1.0000
12.000 1.4020 0.05882 0.05319 -0.0518 0.0207 1.0000
12.250 1.3888 0.06285 0.05749 -0.0498 0.0207 1.0000
12.500 1.3732 0.06732 0.06222 -0.0486 0.0208 1.0000
12.750 1.3557 0.07241 0.06754 -0.0482 0.0209 1.0000
13.000 1.3376 0.07892 0.07429 -0.0484 0.0213 1.0000
13.250 1.3242 0.08336 0.07892 -0.0494 0.0214 1.0000
13.500 1.3096 0.08835 0.08410 -0.0514 0.0215 1.0000
13.750 1.2938 0.09398 0.08992 -0.0542 0.0216 1.0000
14.000 1.2776 0.10016 0.09629 -0.0578 0.0217 1.0000
14.250 1.2601 0.10714 0.10346 -0.0625 0.0219 1.0000
14.500 1.2397 0.11557 0.11210 -0.0687 0.0222 1.0000
14.750 1.2120 0.12706 0.12382 -0.0774 0.0227 1.0000
15.000 1.1179 0.16410 0.16112 -0.1034 0.0261 1.0000
15.250 1.0933 0.18261 0.17954 -0.1125 0.0324 1.0000
15.500 1.1065 0.18103 0.17802 -0.1109 0.0307 1.0000
16.000 0.8302 0.18196 0.17904 -0.0841 0.0612 1.0000
16.250 0.8150 0.18703 0.18409 -0.0885 0.0602 1.0000
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Polar data table (+)
Polar graphs
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