BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BE50 (smoothed) (be50sm-il) Reynolds number: 500,000 Max Cl/Cd: 104.87 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50sm-il-500000.txt Download as CSV file: xf-be50sm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3655 0.08462 0.08249 -0.0219 1.0000 0.0185
-7.000 -0.3693 0.08232 0.08025 -0.0213 1.0000 0.0189
-6.750 -0.3732 0.07998 0.07795 -0.0210 1.0000 0.0192
-6.500 -0.3764 0.07752 0.07553 -0.0210 1.0000 0.0196
-6.250 -0.3599 0.07295 0.07096 -0.0277 0.9985 0.0206
-6.000 -0.3132 0.06610 0.06405 -0.0425 0.9954 0.0215
-5.750 -0.2727 0.05923 0.05710 -0.0541 0.9924 0.0217
-5.500 -0.2313 0.04683 0.04453 -0.0707 0.9884 0.0224
-5.250 -0.1975 0.04313 0.04074 -0.0763 0.9861 0.0233
-5.000 -0.1582 0.03904 0.03652 -0.0828 0.9844 0.0247
-4.750 -0.0993 0.02356 0.02000 -0.0965 0.9832 0.0198
-4.500 -0.0608 0.01813 0.01382 -0.1003 0.9806 0.0193
-4.250 -0.0243 0.01556 0.01078 -0.1024 0.9778 0.0198
-4.000 0.0135 0.01353 0.00836 -0.1045 0.9756 0.0204
-3.750 0.0538 0.01249 0.00712 -0.1069 0.9733 0.0216
-3.500 0.0950 0.01073 0.00516 -0.1097 0.9707 0.0246
-3.250 0.1282 0.01029 0.00468 -0.1106 0.9633 0.0281
-3.000 0.1621 0.00959 0.00390 -0.1117 0.9577 0.0322
-2.750 0.1919 0.00917 0.00346 -0.1118 0.9499 0.0369
-2.500 0.2220 0.00882 0.00305 -0.1120 0.9425 0.0421
-2.250 0.2499 0.00843 0.00265 -0.1117 0.9322 0.0508
-2.000 0.2779 0.00813 0.00234 -0.1114 0.9220 0.0652
-1.750 0.3057 0.00782 0.00210 -0.1112 0.9112 0.0923
-1.500 0.3331 0.00757 0.00193 -0.1108 0.8991 0.1318
-1.250 0.3604 0.00732 0.00181 -0.1106 0.8857 0.1882
-1.000 0.3879 0.00701 0.00174 -0.1104 0.8713 0.2812
-0.750 0.4152 0.00673 0.00173 -0.1103 0.8553 0.4002
-0.500 0.4425 0.00657 0.00171 -0.1100 0.8380 0.4802
0.000 0.4954 0.00600 0.00170 -0.1091 0.8002 0.7209
0.250 0.5157 0.00551 0.00160 -0.1068 0.7794 1.0000
0.500 0.5430 0.00564 0.00157 -0.1064 0.7574 1.0000
0.750 0.5704 0.00578 0.00157 -0.1061 0.7336 1.0000
1.000 0.5976 0.00593 0.00158 -0.1058 0.7092 1.0000
1.250 0.6247 0.00611 0.00160 -0.1055 0.6834 1.0000
1.500 0.6517 0.00630 0.00164 -0.1052 0.6564 1.0000
1.750 0.6786 0.00651 0.00170 -0.1048 0.6273 1.0000
2.000 0.7054 0.00673 0.00178 -0.1045 0.5966 1.0000
2.250 0.7320 0.00698 0.00187 -0.1042 0.5639 1.0000
2.500 0.7584 0.00726 0.00198 -0.1039 0.5288 1.0000
2.750 0.7848 0.00756 0.00211 -0.1036 0.4925 1.0000
3.000 0.8109 0.00788 0.00227 -0.1032 0.4576 1.0000
3.250 0.8372 0.00820 0.00244 -0.1030 0.4274 1.0000
3.500 0.8635 0.00851 0.00262 -0.1027 0.4023 1.0000
3.750 0.8901 0.00879 0.00281 -0.1024 0.3811 1.0000
4.000 0.9167 0.00907 0.00303 -0.1022 0.3634 1.0000
4.250 0.9432 0.00934 0.00324 -0.1020 0.3475 1.0000
4.500 0.9697 0.00961 0.00346 -0.1017 0.3333 1.0000
4.750 0.9962 0.00986 0.00369 -0.1015 0.3200 1.0000
5.000 1.0227 0.01012 0.00394 -0.1013 0.3075 1.0000
5.250 1.0491 0.01038 0.00419 -0.1010 0.2954 1.0000
5.500 1.0754 0.01065 0.00444 -0.1007 0.2827 1.0000
5.750 1.1011 0.01095 0.00467 -0.1004 0.2624 1.0000
6.000 1.1269 0.01126 0.00494 -0.1001 0.2423 1.0000
6.250 1.1526 0.01157 0.00522 -0.0998 0.2264 1.0000
6.500 1.1781 0.01191 0.00553 -0.0994 0.2097 1.0000
6.750 1.2029 0.01232 0.00587 -0.0990 0.1892 1.0000
7.000 1.2271 0.01281 0.00626 -0.0985 0.1637 1.0000
7.250 1.2503 0.01343 0.00676 -0.0979 0.1306 1.0000
7.500 1.2687 0.01474 0.00765 -0.0967 0.0681 1.0000
7.750 1.2858 0.01629 0.00891 -0.0952 0.0291 1.0000
8.000 1.3070 0.01717 0.00983 -0.0941 0.0230 1.0000
8.250 1.3278 0.01808 0.01085 -0.0929 0.0201 1.0000
8.500 1.3491 0.01882 0.01168 -0.0919 0.0181 1.0000
8.750 1.3683 0.01980 0.01274 -0.0907 0.0160 1.0000
9.000 1.3819 0.02139 0.01449 -0.0885 0.0145 1.0000
9.250 1.4011 0.02223 0.01543 -0.0872 0.0137 1.0000
9.500 1.4181 0.02326 0.01657 -0.0856 0.0128 1.0000
9.750 1.4338 0.02436 0.01777 -0.0839 0.0120 1.0000
10.000 1.4475 0.02557 0.01906 -0.0820 0.0113 1.0000
10.250 1.4559 0.02724 0.02083 -0.0794 0.0106 1.0000
10.500 1.4501 0.03038 0.02416 -0.0749 0.0100 1.0000
10.750 1.4608 0.03127 0.02519 -0.0725 0.0097 1.0000
11.000 1.4691 0.03243 0.02648 -0.0700 0.0093 1.0000
11.250 1.4740 0.03400 0.02819 -0.0673 0.0090 1.0000
11.500 1.4766 0.03588 0.03022 -0.0646 0.0087 1.0000
11.750 1.4781 0.03795 0.03243 -0.0621 0.0085 1.0000
12.000 1.4785 0.04022 0.03486 -0.0599 0.0083 1.0000
12.250 1.4781 0.04264 0.03743 -0.0580 0.0081 1.0000
12.500 1.4759 0.04538 0.04033 -0.0563 0.0079 1.0000
12.750 1.4728 0.04833 0.04344 -0.0551 0.0078 1.0000
13.000 1.4677 0.05169 0.04697 -0.0543 0.0077 1.0000
13.250 1.4617 0.05533 0.05077 -0.0539 0.0076 1.0000
13.500 1.4540 0.05937 0.05498 -0.0541 0.0075 1.0000
13.750 1.4446 0.06389 0.05967 -0.0547 0.0074 1.0000
14.000 1.4340 0.06880 0.06474 -0.0559 0.0074 1.0000
14.250 1.4211 0.07430 0.07042 -0.0575 0.0073 1.0000
14.500 1.4068 0.08032 0.07663 -0.0598 0.0073 1.0000
14.750 1.3926 0.08657 0.08304 -0.0625 0.0073 1.0000
15.000 1.3753 0.09376 0.09043 -0.0659 0.0073 1.0000
15.250 1.3582 0.10130 0.09815 -0.0697 0.0073 1.0000
15.500 1.3364 0.11014 0.10720 -0.0744 0.0074 1.0000
15.750 1.3169 0.11888 0.11611 -0.0793 0.0075 1.0000
16.000 1.2932 0.12907 0.12649 -0.0853 0.0076 1.0000
16.250 1.2627 0.14175 0.13941 -0.0931 0.0078 1.0000
16.500 1.2317 0.15568 0.15353 -0.1020 0.0081 1.0000
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Polar data table (+)
Polar graphs
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