BE50 (original) (be50-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: BE50 (original) (be50-il) Reynolds number: 500,000 Max Cl/Cd: 102.14 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-be50-il-500000.txt Download as CSV file: xf-be50-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3878 0.08663 0.08449 -0.0244 1.0000 0.0191
-8.250 -0.3873 0.08465 0.08253 -0.0230 1.0000 0.0195
-8.000 -0.3858 0.08250 0.08042 -0.0223 1.0000 0.0198
-7.750 -0.3858 0.08022 0.07817 -0.0220 1.0000 0.0201
-7.500 -0.3856 0.07781 0.07577 -0.0221 1.0000 0.0204
-7.250 -0.3841 0.07519 0.07318 -0.0227 1.0000 0.0209
-7.000 -0.3805 0.07227 0.07028 -0.0241 1.0000 0.0215
-6.250 -0.2501 0.04294 0.04051 -0.0707 0.9923 0.0262
-6.000 -0.2217 0.04198 0.03955 -0.0730 0.9894 0.0277
-5.750 -0.1823 0.03842 0.03585 -0.0790 0.9869 0.0301
-5.500 -0.1270 0.03288 0.02973 -0.0874 0.9849 0.0349
-5.250 -0.0881 0.02483 0.02128 -0.0952 0.9836 0.0378
-5.000 -0.0536 0.02361 0.01995 -0.0974 0.9803 0.0413
-4.750 -0.0100 0.01699 0.01234 -0.1010 0.9780 0.0328
-4.500 0.0288 0.01487 0.00986 -0.1035 0.9756 0.0328
-4.250 0.0682 0.01351 0.00826 -0.1058 0.9734 0.0335
-4.000 0.1061 0.01232 0.00687 -0.1078 0.9711 0.0338
-3.750 0.1396 0.01149 0.00593 -0.1088 0.9663 0.0343
-3.500 0.1717 0.01080 0.00516 -0.1094 0.9601 0.0346
-3.250 0.2039 0.00994 0.00421 -0.1101 0.9541 0.0358
-3.000 0.2321 0.00921 0.00343 -0.1099 0.9444 0.0373
-2.750 0.2600 0.00876 0.00294 -0.1096 0.9339 0.0391
-2.500 0.2874 0.00844 0.00259 -0.1091 0.9216 0.0412
-2.250 0.3144 0.00818 0.00227 -0.1086 0.9068 0.0437
-2.000 0.3414 0.00798 0.00200 -0.1080 0.8889 0.0467
-1.750 0.3687 0.00762 0.00171 -0.1075 0.8680 0.0804
-1.500 0.3957 0.00723 0.00159 -0.1073 0.8417 0.1995
-1.250 0.4227 0.00695 0.00153 -0.1071 0.8141 0.3099
-1.000 0.4497 0.00683 0.00155 -0.1068 0.7877 0.4207
-0.750 0.4767 0.00678 0.00158 -0.1065 0.7628 0.4908
-0.500 0.5037 0.00667 0.00161 -0.1063 0.7399 0.5823
0.000 0.5504 0.00598 0.00160 -0.1037 0.6976 1.0000
0.250 0.5780 0.00613 0.00162 -0.1035 0.6754 1.0000
0.500 0.6054 0.00630 0.00165 -0.1033 0.6541 1.0000
0.750 0.6330 0.00646 0.00169 -0.1032 0.6319 1.0000
1.000 0.6603 0.00663 0.00174 -0.1030 0.6095 1.0000
1.250 0.6877 0.00681 0.00181 -0.1028 0.5852 1.0000
1.500 0.7148 0.00701 0.00189 -0.1026 0.5576 1.0000
1.750 0.7415 0.00726 0.00198 -0.1024 0.5272 1.0000
2.000 0.7682 0.00753 0.00210 -0.1021 0.4959 1.0000
2.250 0.7947 0.00783 0.00224 -0.1019 0.4503 1.0000
2.500 0.8205 0.00824 0.00240 -0.1016 0.4057 1.0000
3.000 0.8734 0.00888 0.00282 -0.1012 0.3660 1.0000
3.500 0.9269 0.00940 0.00327 -0.1009 0.3408 1.0000
3.750 0.9535 0.00967 0.00348 -0.1008 0.3260 1.0000
4.000 0.9799 0.00995 0.00369 -0.1006 0.3080 1.0000
4.250 1.0066 0.01019 0.00392 -0.1004 0.2934 1.0000
4.500 1.0333 0.01041 0.00412 -0.1003 0.2778 1.0000
4.750 1.0598 0.01065 0.00433 -0.1001 0.2599 1.0000
5.000 1.0857 0.01097 0.00456 -0.0999 0.2368 1.0000
5.250 1.1109 0.01139 0.00486 -0.0996 0.2063 1.0000
5.500 1.1352 0.01192 0.00524 -0.0992 0.1733 1.0000
5.750 1.1580 0.01271 0.00576 -0.0986 0.1266 1.0000
6.000 1.1737 0.01460 0.00700 -0.0972 0.0289 1.0000
6.250 1.1965 0.01539 0.00777 -0.0964 0.0179 1.0000
6.500 1.2204 0.01600 0.00845 -0.0957 0.0160 1.0000
6.750 1.2435 0.01666 0.00920 -0.0950 0.0148 1.0000
7.000 1.2655 0.01749 0.01011 -0.0941 0.0137 1.0000
7.250 1.2847 0.01865 0.01141 -0.0927 0.0128 1.0000
7.500 1.3035 0.01978 0.01266 -0.0914 0.0121 1.0000
7.750 1.3234 0.02069 0.01368 -0.0902 0.0116 1.0000
8.000 1.3411 0.02182 0.01492 -0.0888 0.0113 1.0000
8.250 1.3576 0.02304 0.01625 -0.0871 0.0109 1.0000
8.500 1.3728 0.02435 0.01767 -0.0853 0.0106 1.0000
8.750 1.3869 0.02576 0.01919 -0.0834 0.0103 1.0000
9.000 1.3999 0.02726 0.02080 -0.0814 0.0101 1.0000
9.250 1.4118 0.02890 0.02257 -0.0792 0.0099 1.0000
9.500 1.4225 0.03069 0.02449 -0.0770 0.0097 1.0000
9.750 1.4323 0.03266 0.02661 -0.0747 0.0097 1.0000
10.000 1.4404 0.03489 0.02902 -0.0721 0.0097 1.0000
10.250 1.4458 0.03742 0.03177 -0.0692 0.0099 1.0000
10.500 1.4484 0.03993 0.03450 -0.0662 0.0099 1.0000
10.750 1.4484 0.04240 0.03717 -0.0632 0.0099 1.0000
11.000 1.4489 0.04451 0.03939 -0.0608 0.0097 1.0000
11.250 1.4453 0.04712 0.04218 -0.0583 0.0096 1.0000
11.500 1.4185 0.05366 0.04932 -0.0545 0.0107 1.0000
11.750 1.3994 0.05891 0.05485 -0.0528 0.0113 1.0000
12.000 1.3786 0.06454 0.06071 -0.0522 0.0117 1.0000
12.250 1.2445 0.06070 0.05699 -0.0404 0.0106 1.0000
12.500 1.2208 0.06714 0.06363 -0.0407 0.0107 1.0000
12.750 1.1951 0.07406 0.07074 -0.0417 0.0110 1.0000
13.000 1.1719 0.08054 0.07738 -0.0433 0.0110 1.0000
13.250 1.1473 0.08733 0.08433 -0.0455 0.0111 1.0000
13.500 1.1230 0.09409 0.09125 -0.0481 0.0112 1.0000
13.750 1.0931 0.10147 0.09877 -0.0511 0.0115 1.0000
14.000 1.0597 0.10772 0.10516 -0.0536 0.0117 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BE50 (original) (be50-il)