MRC-20 (mrc-20-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MRC-20 (mrc-20-il) Reynolds number: 50,000 Max Cl/Cd: 23.9 at α=11.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mrc-20-il-50000.txt Download as CSV file: xf-mrc-20-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MRC-20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3681 0.12078 0.11429 -0.0234 1.0000 0.3099
-9.000 -0.3746 0.11923 0.11282 -0.0209 1.0000 0.3292
-8.750 -0.3905 0.11831 0.11201 -0.0181 1.0000 0.3472
-8.500 -0.3675 0.11525 0.10896 -0.0153 1.0000 0.3765
-8.250 -0.3546 0.11277 0.10651 -0.0125 1.0000 0.4044
-8.000 -0.3745 0.11256 0.10642 -0.0086 1.0000 0.4270
-7.750 -0.3587 0.11001 0.10390 -0.0058 1.0000 0.4588
-7.500 -0.3398 0.10702 0.10094 -0.0036 1.0000 0.4893
-7.250 -0.3301 0.10443 0.09839 -0.0013 1.0000 0.5159
-7.000 -0.3440 0.10411 0.09815 0.0032 1.0000 0.5426
-6.750 -0.3162 0.09984 0.09389 0.0035 1.0000 0.5681
-6.500 -0.3151 0.09785 0.09196 0.0061 1.0000 0.5896
-5.000 -0.4761 0.08466 0.07949 0.0223 1.0000 0.5057
-4.750 -0.5439 0.07998 0.07500 0.0229 1.0000 0.4643
-4.500 -0.5918 0.05633 0.04997 -0.0128 1.0000 0.2767
-4.250 -0.5549 0.05209 0.04413 -0.0173 1.0000 0.1999
-4.000 -0.5266 0.05045 0.04157 -0.0169 1.0000 0.1673
-3.750 -0.5023 0.04834 0.03895 -0.0160 1.0000 0.1497
-3.500 -0.4798 0.04582 0.03614 -0.0154 1.0000 0.1388
-3.250 -0.4566 0.04458 0.03446 -0.0144 1.0000 0.1304
-3.000 -0.4339 0.04292 0.03253 -0.0136 1.0000 0.1247
-2.750 -0.4105 0.04217 0.03121 -0.0124 1.0000 0.1193
-2.500 -0.3887 0.04128 0.03007 -0.0115 1.0000 0.1186
-2.250 -0.3669 0.04003 0.02874 -0.0109 1.0000 0.1200
-2.000 -0.3450 0.03913 0.02780 -0.0101 1.0000 0.1216
-1.750 -0.3229 0.03848 0.02712 -0.0092 1.0000 0.1228
-1.500 -0.3011 0.03801 0.02666 -0.0082 1.0000 0.1250
-1.250 -0.2799 0.03776 0.02635 -0.0073 1.0000 0.1305
-1.000 -0.2588 0.03744 0.02601 -0.0067 1.0000 0.1380
-0.750 -0.2376 0.03725 0.02573 -0.0063 1.0000 0.1480
-0.500 -0.2149 0.03699 0.02544 -0.0065 1.0000 0.1671
-0.250 -0.1849 0.03476 0.02589 -0.0070 1.0000 0.6489
0.000 -0.1651 0.03495 0.02690 -0.0009 1.0000 1.0000
0.500 -0.0589 0.03848 0.02927 -0.0144 0.9640 1.0000
0.750 -0.0123 0.03998 0.03040 -0.0197 0.9471 1.0000
1.000 0.0288 0.04126 0.03139 -0.0237 0.9313 1.0000
1.250 0.0611 0.04222 0.03212 -0.0261 0.9167 1.0000
1.500 0.0921 0.04315 0.03285 -0.0282 0.9022 1.0000
1.750 0.1201 0.04405 0.03359 -0.0297 0.8884 1.0000
2.000 0.1486 0.04498 0.03437 -0.0312 0.8744 1.0000
2.250 0.1762 0.04594 0.03520 -0.0326 0.8610 1.0000
2.500 0.2049 0.04690 0.03605 -0.0340 0.8475 1.0000
2.750 0.2348 0.04790 0.03694 -0.0355 0.8345 1.0000
3.000 0.2686 0.04890 0.03784 -0.0376 0.8218 1.0000
3.250 0.3011 0.04985 0.03872 -0.0393 0.8091 1.0000
3.500 0.3197 0.05079 0.03961 -0.0391 0.7956 1.0000
3.750 0.3409 0.05179 0.04058 -0.0393 0.7824 1.0000
4.000 0.3645 0.05283 0.04158 -0.0398 0.7696 1.0000
4.250 0.3933 0.05380 0.04252 -0.0408 0.7571 1.0000
4.500 0.4325 0.05457 0.04328 -0.0430 0.7457 1.0000
4.750 0.4455 0.05575 0.04446 -0.0421 0.7320 1.0000
5.000 0.4605 0.05702 0.04574 -0.0415 0.7190 1.0000
5.250 0.4812 0.05816 0.04690 -0.0415 0.7062 1.0000
5.500 0.5104 0.05909 0.04785 -0.0423 0.6944 1.0000
5.750 0.5426 0.05980 0.04862 -0.0432 0.6825 1.0000
6.000 0.5504 0.06145 0.05029 -0.0420 0.6690 1.0000
6.250 0.5636 0.06297 0.05185 -0.0413 0.6561 1.0000
6.500 0.5846 0.06420 0.05313 -0.0412 0.6438 1.0000
7.000 0.6330 0.06623 0.05531 -0.0413 0.6192 1.0000
7.250 0.6378 0.06837 0.05750 -0.0401 0.6061 1.0000
7.500 0.6515 0.07003 0.05922 -0.0395 0.5933 1.0000
7.750 0.6787 0.07090 0.06018 -0.0396 0.5816 1.0000
8.000 0.7096 0.07134 0.06075 -0.0396 0.5694 1.0000
8.250 0.7047 0.07437 0.06384 -0.0382 0.5559 1.0000
8.500 0.7096 0.07678 0.06631 -0.0373 0.5429 1.0000
8.750 0.7250 0.07845 0.06808 -0.0368 0.5306 1.0000
9.000 0.7625 0.07825 0.06804 -0.0366 0.5186 1.0000
9.250 0.7690 0.08056 0.07044 -0.0358 0.5055 1.0000
9.500 0.7580 0.08459 0.07452 -0.0349 0.4927 1.0000
9.750 0.7634 0.08718 0.07719 -0.0342 0.4801 1.0000
10.000 0.7836 0.08848 0.07861 -0.0336 0.4679 1.0000
10.250 0.8245 0.08742 0.07775 -0.0326 0.4548 1.0000
10.500 0.7992 0.09332 0.08367 -0.0323 0.4426 1.0000
10.750 0.7907 0.09756 0.08797 -0.0320 0.4309 1.0000
11.500 1.1760 0.05836 0.05009 -0.0242 0.3757 1.0000
11.750 1.2630 0.05284 0.04458 -0.0260 0.3426 1.0000
12.000 1.1932 0.06008 0.05199 -0.0193 0.3410 1.0000
12.250 1.2614 0.05562 0.04750 -0.0193 0.3085 1.0000
12.500 0.8666 0.11265 0.10388 -0.0274 0.3431 1.0000
12.750 0.8180 0.12318 0.11432 -0.0307 0.3389 1.0000
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Polar data table (+)
Polar graphs
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