BE50 (original) (be50-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.08 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50-il-1000000-n5.txt Download as CSV file: xf-be50-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BE50 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4668 0.13830 0.13661 -0.0002 1.0000 0.0033
-10.500 -0.6310 0.02457 0.02213 -0.0948 0.9959 0.0050
-10.250 -0.6011 0.01977 0.01680 -0.0997 0.9945 0.0053
-10.000 -0.5710 0.01769 0.01440 -0.1018 0.9925 0.0057
-9.750 -0.5399 0.01617 0.01263 -0.1036 0.9905 0.0060
-9.500 -0.5085 0.01498 0.01123 -0.1050 0.9883 0.0062
-9.250 -0.4770 0.01400 0.01010 -0.1063 0.9865 0.0070
-9.000 -0.4475 0.01330 0.00931 -0.1070 0.9841 0.0077
-8.750 -0.4184 0.01271 0.00862 -0.1075 0.9814 0.0085
-8.500 -0.3888 0.01216 0.00797 -0.1080 0.9789 0.0093
-8.250 -0.3585 0.01217 0.00802 -0.1084 0.9765 0.0104
-8.000 -0.3301 0.01212 0.00798 -0.1084 0.9729 0.0114
-7.750 -0.3017 0.01186 0.00766 -0.1085 0.9692 0.0123
-7.500 -0.2731 0.01159 0.00731 -0.1086 0.9656 0.0129
-7.250 -0.2454 0.01120 0.00684 -0.1086 0.9609 0.0134
-7.000 -0.2180 0.01109 0.00673 -0.1084 0.9550 0.0141
-6.750 -0.1905 0.01119 0.00684 -0.1081 0.9498 0.0147
-6.500 -0.1631 0.01113 0.00677 -0.1079 0.9438 0.0153
-6.250 -0.1359 0.01088 0.00645 -0.1076 0.9371 0.0160
-6.000 -0.1083 0.01063 0.00614 -0.1075 0.9290 0.0167
-5.750 -0.0808 0.01040 0.00583 -0.1073 0.9214 0.0174
-5.500 -0.0532 0.01008 0.00542 -0.1071 0.9110 0.0178
-5.250 -0.0260 0.00988 0.00514 -0.1068 0.8960 0.0182
-5.000 0.0011 0.00964 0.00477 -0.1065 0.8754 0.0185
-4.750 0.0281 0.00937 0.00434 -0.1061 0.8498 0.0186
-4.500 0.0555 0.00892 0.00368 -0.1059 0.8197 0.0192
-4.250 0.0835 0.00838 0.00292 -0.1059 0.7923 0.0201
-4.000 0.1115 0.00816 0.00255 -0.1059 0.7667 0.0209
-3.750 0.1395 0.00805 0.00229 -0.1058 0.7402 0.0215
-3.500 0.1677 0.00795 0.00207 -0.1058 0.7177 0.0221
-3.250 0.1960 0.00788 0.00189 -0.1058 0.6979 0.0226
-3.000 0.2243 0.00780 0.00171 -0.1058 0.6807 0.0231
-2.750 0.2527 0.00774 0.00155 -0.1058 0.6628 0.0236
-2.500 0.2811 0.00770 0.00142 -0.1059 0.6433 0.0240
-2.250 0.3095 0.00767 0.00130 -0.1059 0.6260 0.0246
-2.000 0.3378 0.00766 0.00120 -0.1059 0.6082 0.0255
-1.750 0.3660 0.00767 0.00112 -0.1059 0.5885 0.0266
-1.500 0.3942 0.00770 0.00106 -0.1059 0.5665 0.0275
-1.250 0.4223 0.00774 0.00101 -0.1059 0.5451 0.0314
-1.000 0.4505 0.00777 0.00099 -0.1059 0.5267 0.0412
-0.750 0.4789 0.00768 0.00099 -0.1061 0.5098 0.0952
-0.500 0.5070 0.00766 0.00102 -0.1062 0.4896 0.1394
-0.250 0.5346 0.00779 0.00106 -0.1062 0.4431 0.1688
0.000 0.5615 0.00804 0.00114 -0.1062 0.3897 0.2001
0.250 0.5895 0.00794 0.00125 -0.1065 0.3650 0.3223
0.750 0.6455 0.00794 0.00147 -0.1068 0.3372 0.4631
1.000 0.6736 0.00795 0.00157 -0.1068 0.3289 0.5128
1.250 0.7015 0.00798 0.00167 -0.1069 0.3198 0.5581
1.750 0.7508 0.00729 0.00187 -0.1055 0.3013 1.0000
2.000 0.7785 0.00745 0.00197 -0.1055 0.2907 1.0000
2.250 0.8064 0.00758 0.00206 -0.1055 0.2813 1.0000
2.500 0.8341 0.00772 0.00216 -0.1055 0.2731 1.0000
2.750 0.8617 0.00786 0.00228 -0.1055 0.2639 1.0000
3.000 0.8888 0.00809 0.00241 -0.1054 0.2437 1.0000
3.250 0.9159 0.00832 0.00255 -0.1053 0.2261 1.0000
3.500 0.9425 0.00861 0.00274 -0.1052 0.2047 1.0000
3.750 0.9687 0.00896 0.00297 -0.1050 0.1792 1.0000
4.000 0.9950 0.00929 0.00319 -0.1049 0.1587 1.0000
4.250 1.0201 0.00980 0.00351 -0.1046 0.1240 1.0000
4.500 1.0415 0.01092 0.00419 -0.1038 0.0455 1.0000
4.750 1.0666 0.01143 0.00460 -0.1035 0.0233 1.0000
5.000 1.0918 0.01189 0.00500 -0.1031 0.0108 1.0000
5.250 1.1175 0.01225 0.00537 -0.1028 0.0087 1.0000
5.500 1.1433 0.01259 0.00574 -0.1025 0.0076 1.0000
5.750 1.1690 0.01291 0.00611 -0.1022 0.0070 1.0000
6.000 1.1945 0.01327 0.00650 -0.1019 0.0064 1.0000
6.250 1.2195 0.01366 0.00693 -0.1016 0.0058 1.0000
6.500 1.2437 0.01419 0.00749 -0.1011 0.0051 1.0000
6.750 1.2682 0.01463 0.00798 -0.1006 0.0048 1.0000
7.000 1.2925 0.01508 0.00847 -0.1002 0.0045 1.0000
7.250 1.3164 0.01557 0.00903 -0.0996 0.0042 1.0000
7.500 1.3399 0.01609 0.00959 -0.0991 0.0040 1.0000
7.750 1.3631 0.01663 0.01018 -0.0985 0.0037 1.0000
8.000 1.3858 0.01719 0.01079 -0.0978 0.0035 1.0000
8.250 1.4076 0.01784 0.01149 -0.0971 0.0034 1.0000
8.500 1.4271 0.01876 0.01250 -0.0959 0.0031 1.0000
8.750 1.4462 0.01967 0.01353 -0.0947 0.0030 1.0000
9.000 1.4663 0.02039 0.01432 -0.0938 0.0029 1.0000
9.250 1.4858 0.02113 0.01515 -0.0927 0.0028 1.0000
9.500 1.5044 0.02191 0.01601 -0.0915 0.0027 1.0000
9.750 1.5221 0.02274 0.01692 -0.0902 0.0026 1.0000
10.000 1.5387 0.02362 0.01789 -0.0888 0.0024 1.0000
10.250 1.5535 0.02459 0.01895 -0.0871 0.0023 1.0000
10.500 1.5669 0.02562 0.02007 -0.0853 0.0023 1.0000
10.750 1.5784 0.02667 0.02122 -0.0832 0.0022 1.0000
11.000 1.5861 0.02773 0.02239 -0.0805 0.0021 1.0000
11.250 1.5919 0.02888 0.02363 -0.0776 0.0021 1.0000
11.500 1.5962 0.03021 0.02506 -0.0749 0.0021 1.0000
11.750 1.5998 0.03167 0.02663 -0.0723 0.0020 1.0000
12.000 1.6015 0.03340 0.02847 -0.0700 0.0020 1.0000
12.250 1.6026 0.03533 0.03051 -0.0679 0.0019 1.0000
12.500 1.6012 0.03764 0.03295 -0.0662 0.0019 1.0000
12.750 1.5981 0.04037 0.03581 -0.0648 0.0019 1.0000
13.000 1.5926 0.04362 0.03920 -0.0641 0.0019 1.0000
13.250 1.5847 0.04750 0.04323 -0.0639 0.0018 1.0000
13.500 1.5749 0.05195 0.04783 -0.0644 0.0018 1.0000
13.750 1.5616 0.05721 0.05326 -0.0656 0.0018 1.0000
14.000 1.5480 0.06278 0.05899 -0.0672 0.0018 1.0000
14.250 1.5311 0.06916 0.06553 -0.0693 0.0018 1.0000
14.500 1.5141 0.07577 0.07229 -0.0717 0.0018 1.0000
14.750 1.4959 0.08284 0.07952 -0.0745 0.0017 1.0000
15.000 1.4774 0.09028 0.08710 -0.0777 0.0017 1.0000
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Polar data table (+)
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