BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 200,000 Max Cl/Cd: 74.36 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50sm-il-200000-n5.txt Download as CSV file: xf-be50sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3721 0.09684 0.09328 -0.0225 1.0000 0.0228
-8.000 -0.3681 0.09376 0.09024 -0.0234 1.0000 0.0229
-7.750 -0.3662 0.09073 0.08726 -0.0243 1.0000 0.0229
-7.500 -0.2865 0.07504 0.07184 -0.0273 1.0000 0.0199
-7.250 -0.2916 0.07222 0.06908 -0.0262 1.0000 0.0192
-7.000 -0.3647 0.08253 0.07920 -0.0242 1.0000 0.0196
-6.750 -0.3647 0.07944 0.07616 -0.0250 1.0000 0.0185
-6.500 -0.3649 0.07580 0.07257 -0.0267 1.0000 0.0175
-6.000 -0.3359 0.06231 0.05904 -0.0421 0.9970 0.0153
-5.500 -0.2633 0.05031 0.04686 -0.0616 0.9885 0.0166
-5.250 -0.2217 0.04454 0.04090 -0.0709 0.9850 0.0179
-5.000 -0.1659 0.03073 0.02629 -0.0860 0.9825 0.0172
-4.750 -0.1243 0.02342 0.01801 -0.0920 0.9792 0.0174
-4.500 -0.0870 0.02027 0.01423 -0.0949 0.9759 0.0183
-4.250 -0.0498 0.01809 0.01154 -0.0972 0.9731 0.0195
-4.000 -0.0123 0.01669 0.00977 -0.0993 0.9707 0.0214
-3.750 0.0216 0.01567 0.00863 -0.1008 0.9665 0.0242
-3.500 0.0559 0.01478 0.00759 -0.1022 0.9619 0.0267
-3.250 0.0918 0.01400 0.00664 -0.1037 0.9581 0.0297
-3.000 0.1256 0.01331 0.00593 -0.1050 0.9530 0.0347
-2.750 0.1592 0.01274 0.00527 -0.1060 0.9457 0.0392
-2.500 0.1932 0.01218 0.00468 -0.1071 0.9355 0.0470
-2.250 0.2268 0.01169 0.00414 -0.1080 0.9231 0.0562
-2.000 0.2587 0.01130 0.00376 -0.1086 0.9110 0.0723
-1.750 0.2896 0.01097 0.00346 -0.1090 0.8998 0.0963
-1.500 0.3191 0.01066 0.00323 -0.1091 0.8869 0.1334
-1.250 0.3482 0.01036 0.00305 -0.1092 0.8730 0.1827
-1.000 0.3770 0.01001 0.00291 -0.1093 0.8583 0.2620
-0.750 0.4051 0.00967 0.00286 -0.1093 0.8422 0.3743
-0.500 0.4325 0.00944 0.00281 -0.1089 0.8244 0.4635
-0.250 0.4593 0.00924 0.00274 -0.1084 0.8054 0.5399
0.000 0.4844 0.00889 0.00268 -0.1075 0.7860 0.6548
0.500 0.5325 0.00841 0.00244 -0.1046 0.7422 1.0000
0.750 0.5596 0.00855 0.00241 -0.1041 0.7181 1.0000
1.000 0.5865 0.00871 0.00240 -0.1037 0.6929 1.0000
1.250 0.6133 0.00890 0.00241 -0.1032 0.6668 1.0000
1.500 0.6398 0.00911 0.00245 -0.1028 0.6391 1.0000
1.750 0.6663 0.00934 0.00251 -0.1023 0.6105 1.0000
2.000 0.6925 0.00960 0.00260 -0.1018 0.5806 1.0000
2.250 0.7186 0.00987 0.00270 -0.1013 0.5496 1.0000
2.500 0.7444 0.01017 0.00283 -0.1009 0.5180 1.0000
2.750 0.7702 0.01049 0.00298 -0.1004 0.4869 1.0000
3.000 0.7959 0.01082 0.00318 -0.1000 0.4577 1.0000
3.250 0.8217 0.01116 0.00339 -0.0996 0.4313 1.0000
3.500 0.8475 0.01149 0.00361 -0.0992 0.4085 1.0000
3.750 0.8733 0.01183 0.00385 -0.0988 0.3888 1.0000
4.000 0.8992 0.01216 0.00414 -0.0984 0.3715 1.0000
4.250 0.9251 0.01249 0.00443 -0.0981 0.3559 1.0000
4.500 0.9509 0.01282 0.00472 -0.0977 0.3417 1.0000
4.750 0.9767 0.01315 0.00504 -0.0974 0.3284 1.0000
5.000 1.0024 0.01350 0.00537 -0.0970 0.3160 1.0000
5.250 1.0281 0.01383 0.00574 -0.0966 0.3037 1.0000
5.500 1.0537 0.01417 0.00610 -0.0962 0.2919 1.0000
5.750 1.0792 0.01452 0.00649 -0.0958 0.2802 1.0000
6.000 1.1044 0.01488 0.00689 -0.0954 0.2687 1.0000
6.250 1.1294 0.01526 0.00733 -0.0949 0.2559 1.0000
6.500 1.1534 0.01570 0.00772 -0.0944 0.2334 1.0000
6.750 1.1770 0.01619 0.00813 -0.0938 0.2055 1.0000
7.000 1.2004 0.01672 0.00861 -0.0932 0.1799 1.0000
7.250 1.2227 0.01739 0.00917 -0.0925 0.1502 1.0000
7.500 1.2438 0.01823 0.00989 -0.0917 0.1140 1.0000
7.750 1.2623 0.01943 0.01084 -0.0906 0.0718 1.0000
8.000 1.2793 0.02084 0.01204 -0.0892 0.0407 1.0000
8.250 1.2974 0.02203 0.01321 -0.0879 0.0293 1.0000
8.500 1.3168 0.02300 0.01431 -0.0866 0.0248 1.0000
8.750 1.3330 0.02431 0.01573 -0.0850 0.0215 1.0000
9.000 1.3502 0.02539 0.01700 -0.0835 0.0197 1.0000
9.250 1.3666 0.02647 0.01823 -0.0820 0.0177 1.0000
9.500 1.3808 0.02770 0.01958 -0.0802 0.0161 1.0000
9.750 1.3890 0.02943 0.02143 -0.0777 0.0150 1.0000
10.000 1.3968 0.03108 0.02323 -0.0752 0.0143 1.0000
10.250 1.4049 0.03253 0.02485 -0.0726 0.0137 1.0000
10.500 1.4106 0.03400 0.02648 -0.0698 0.0130 1.0000
10.750 1.4157 0.03555 0.02817 -0.0673 0.0122 1.0000
11.000 1.4201 0.03719 0.02997 -0.0649 0.0114 1.0000
11.250 1.4226 0.03906 0.03197 -0.0628 0.0109 1.0000
11.500 1.4219 0.04136 0.03439 -0.0606 0.0105 1.0000
11.750 1.4181 0.04418 0.03734 -0.0587 0.0102 1.0000
12.000 1.4133 0.04734 0.04065 -0.0570 0.0099 1.0000
12.250 1.4123 0.05021 0.04372 -0.0558 0.0098 1.0000
12.500 1.4097 0.05339 0.04711 -0.0550 0.0096 1.0000
12.750 1.4058 0.05690 0.05083 -0.0545 0.0094 1.0000
13.000 1.4003 0.06076 0.05490 -0.0545 0.0092 1.0000
13.250 1.3933 0.06500 0.05936 -0.0548 0.0091 1.0000
13.500 1.3849 0.06963 0.06420 -0.0556 0.0090 1.0000
13.750 1.3747 0.07470 0.06949 -0.0570 0.0089 1.0000
14.000 1.3634 0.08018 0.07518 -0.0588 0.0088 1.0000
14.250 1.3508 0.08609 0.08130 -0.0611 0.0087 1.0000
14.500 1.3371 0.09247 0.08788 -0.0639 0.0087 1.0000
14.750 1.3224 0.09935 0.09496 -0.0673 0.0087 1.0000
15.000 1.3073 0.10661 0.10241 -0.0711 0.0087 1.0000
15.250 1.2914 0.11434 0.11033 -0.0753 0.0087 1.0000
15.500 1.2753 0.12247 0.11863 -0.0800 0.0087 1.0000
15.750 1.2589 0.13104 0.12737 -0.0851 0.0087 1.0000
16.000 1.2420 0.14012 0.13661 -0.0906 0.0088 1.0000
16.250 1.2247 0.14979 0.14643 -0.0967 0.0089 1.0000
16.500 1.2069 0.16032 0.15710 -0.1034 0.0090 1.0000
16.750 1.1878 0.17209 0.16899 -0.1108 0.0092 1.0000
17.000 1.1648 0.18653 0.18351 -0.1196 0.0094 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BE50 (smoothed) (be50sm-il)