PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU-90-125WL (psu-90-125wl-il) Reynolds number: 50,000 Max Cl/Cd: 32.22 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu-90-125wl-il-50000.txt Download as CSV file: xf-psu-90-125wl-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: PSU-90-125WL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3624 0.10421 0.09737 -0.0271 1.0000 0.3032
-8.750 -0.3610 0.10164 0.09487 -0.0261 1.0000 0.3145
-8.500 -0.3566 0.09816 0.09146 -0.0254 1.0000 0.3201
-8.250 -0.3553 0.09526 0.08863 -0.0245 1.0000 0.3259
-8.000 -0.3723 0.09340 0.08693 -0.0232 1.0000 0.3333
-7.500 -0.5375 0.07262 0.06662 -0.0401 1.0000 0.1438
-7.250 -0.5747 0.06710 0.06091 -0.0403 1.0000 0.1337
-7.000 -0.5826 0.06300 0.05671 -0.0390 1.0000 0.1287
-6.750 -0.6004 0.05718 0.05027 -0.0389 1.0000 0.1204
-6.500 -0.5959 0.05349 0.04639 -0.0377 1.0000 0.1180
-6.250 -0.5907 0.04965 0.04217 -0.0368 1.0000 0.1160
-6.000 -0.5817 0.04615 0.03820 -0.0359 1.0000 0.1159
-5.750 -0.5688 0.04304 0.03462 -0.0350 1.0000 0.1167
-5.500 -0.5526 0.04016 0.03123 -0.0342 1.0000 0.1182
-5.250 -0.5333 0.03753 0.02807 -0.0333 1.0000 0.1196
-5.000 -0.5120 0.03528 0.02521 -0.0324 1.0000 0.1219
-4.750 -0.4912 0.03326 0.02325 -0.0315 1.0000 0.1278
-4.500 -0.4696 0.03168 0.02137 -0.0305 1.0000 0.1378
-4.250 -0.4481 0.03016 0.01979 -0.0293 1.0000 0.1523
-4.000 -0.4272 0.02866 0.01844 -0.0280 1.0000 0.1779
-3.750 -0.4073 0.02693 0.01711 -0.0267 1.0000 0.2402
-3.500 -0.3912 0.02504 0.01633 -0.0251 1.0000 0.3793
-3.250 -0.3805 0.02421 0.01653 -0.0209 1.0000 0.5311
-3.000 -0.3737 0.02444 0.01714 -0.0151 1.0000 0.6358
-2.750 -0.3692 0.02476 0.01761 -0.0087 1.0000 0.7103
-2.500 -0.3663 0.02494 0.01783 -0.0020 1.0000 0.7729
-2.250 -0.3638 0.02496 0.01787 0.0047 1.0000 0.8315
-2.000 -0.3492 0.02506 0.01790 0.0092 1.0000 0.8986
-1.750 -0.1613 0.02747 0.01928 -0.0183 1.0000 0.9951
-1.500 -0.1616 0.02678 0.01846 -0.0173 1.0000 1.0000
-1.250 -0.1742 0.02596 0.01756 -0.0136 1.0000 1.0000
-1.000 -0.1800 0.02534 0.01681 -0.0108 1.0000 1.0000
-0.750 -0.1726 0.02516 0.01643 -0.0098 1.0000 1.0000
-0.500 -0.1576 0.02530 0.01634 -0.0099 1.0000 1.0000
-0.250 -0.1397 0.02562 0.01642 -0.0102 1.0000 1.0000
0.000 -0.1209 0.02606 0.01665 -0.0106 1.0000 1.0000
0.250 -0.1018 0.02658 0.01699 -0.0110 1.0000 1.0000
0.500 -0.0766 0.02737 0.01760 -0.0125 0.9973 1.0000
0.750 -0.0244 0.02911 0.01910 -0.0189 0.9831 1.0000
1.000 0.0188 0.03039 0.02023 -0.0235 0.9686 1.0000
1.250 0.0597 0.03162 0.02131 -0.0275 0.9542 1.0000
1.500 0.0988 0.03277 0.02235 -0.0311 0.9395 1.0000
1.750 0.1365 0.03387 0.02336 -0.0343 0.9246 1.0000
2.000 0.1729 0.03493 0.02435 -0.0371 0.9092 1.0000
2.250 0.2082 0.03596 0.02533 -0.0397 0.8937 1.0000
2.500 0.2429 0.03696 0.02629 -0.0419 0.8777 1.0000
2.750 0.2767 0.03793 0.02724 -0.0440 0.8616 1.0000
3.000 0.3101 0.03888 0.02819 -0.0458 0.8452 1.0000
3.250 0.3433 0.03979 0.02912 -0.0475 0.8288 1.0000
3.500 0.3774 0.04066 0.03001 -0.0491 0.8121 1.0000
3.750 0.4123 0.04146 0.03085 -0.0507 0.7954 1.0000
4.000 0.4484 0.04218 0.03164 -0.0522 0.7788 1.0000
4.250 0.4857 0.04278 0.03231 -0.0537 0.7624 1.0000
4.500 0.5105 0.04354 0.03314 -0.0536 0.7445 1.0000
4.750 0.5344 0.04430 0.03399 -0.0534 0.7262 1.0000
5.000 0.5642 0.04485 0.03464 -0.0536 0.7084 1.0000
5.250 0.5985 0.04514 0.03504 -0.0540 0.6910 1.0000
5.500 0.6368 0.04512 0.03518 -0.0545 0.6741 1.0000
5.750 0.6795 0.04464 0.03487 -0.0551 0.6577 1.0000
6.000 0.7039 0.04496 0.03531 -0.0540 0.6387 1.0000
6.250 0.7306 0.04505 0.03557 -0.0530 0.6197 1.0000
6.500 0.7775 0.04357 0.03431 -0.0528 0.6027 1.0000
6.750 0.8424 0.04072 0.03177 -0.0536 0.5858 1.0000
7.000 0.9160 0.03706 0.02837 -0.0549 0.5668 1.0000
7.250 0.9485 0.03628 0.02776 -0.0535 0.5427 1.0000
7.500 0.9944 0.03474 0.02634 -0.0531 0.5162 1.0000
7.750 1.0339 0.03384 0.02547 -0.0524 0.4869 1.0000
8.000 1.0649 0.03367 0.02530 -0.0512 0.4566 1.0000
8.250 1.0908 0.03396 0.02555 -0.0496 0.4262 1.0000
8.500 1.1133 0.03455 0.02608 -0.0479 0.3961 1.0000
8.750 1.1336 0.03539 0.02686 -0.0460 0.3671 1.0000
9.000 1.1525 0.03637 0.02779 -0.0441 0.3388 1.0000
9.250 1.1716 0.03748 0.02878 -0.0423 0.3113 1.0000
9.500 1.1862 0.03885 0.03014 -0.0402 0.2860 1.0000
9.750 1.1962 0.04049 0.03183 -0.0376 0.2632 1.0000
10.000 1.2162 0.04198 0.03312 -0.0363 0.2390 1.0000
10.250 1.2204 0.04403 0.03537 -0.0333 0.2204 1.0000
10.500 1.2289 0.04596 0.03738 -0.0308 0.2013 1.0000
10.750 1.2446 0.04798 0.03922 -0.0292 0.1810 1.0000
11.000 1.2461 0.05025 0.04163 -0.0262 0.1658 1.0000
11.250 1.2464 0.05249 0.04396 -0.0233 0.1515 1.0000
11.500 1.2469 0.05480 0.04629 -0.0206 0.1381 1.0000
11.750 1.2494 0.05719 0.04865 -0.0182 0.1256 1.0000
12.000 1.2278 0.06034 0.05226 -0.0139 0.1226 1.0000
12.250 1.2342 0.06312 0.05495 -0.0123 0.1120 1.0000
12.500 1.2099 0.06689 0.05910 -0.0092 0.1106 1.0000
12.750 1.1851 0.07119 0.06373 -0.0072 0.1097 1.0000
13.000 1.1588 0.07609 0.06892 -0.0062 0.1095 1.0000
13.250 1.1314 0.08174 0.07481 -0.0064 0.1101 1.0000
13.500 1.1021 0.08824 0.08150 -0.0078 0.1110 1.0000
13.750 1.0741 0.09543 0.08884 -0.0101 0.1121 1.0000
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Polar data table (+)
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