PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU-90-125WL (psu-90-125wl-il) Reynolds number: 100,000 Max Cl/Cd: 54.1 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu-90-125wl-il-100000.txt Download as CSV file: xf-psu-90-125wl-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3843 0.10759 0.10254 -0.0394 1.0000 0.1273
-10.000 -0.3843 0.10458 0.09958 -0.0399 1.0000 0.1318
-9.750 -0.4431 0.10173 0.09699 -0.0481 1.0000 0.1364
-9.500 -0.4005 0.09741 0.09258 -0.0424 1.0000 0.1390
-9.250 -0.3915 0.09467 0.08987 -0.0411 1.0000 0.1425
-9.000 -0.4017 0.09172 0.08702 -0.0419 1.0000 0.1479
-8.750 -0.4434 0.08796 0.08349 -0.0446 1.0000 0.1521
-8.500 -0.4220 0.08535 0.08086 -0.0412 1.0000 0.1548
-8.250 -0.4256 0.08327 0.07885 -0.0391 1.0000 0.1593
-8.000 -0.4535 0.08134 0.07708 -0.0367 1.0000 0.1614
-7.750 -0.5011 0.08033 0.07625 -0.0329 1.0000 0.1630
-7.000 -0.6309 0.05364 0.04863 -0.0378 1.0000 0.0842
-6.750 -0.6372 0.04530 0.03906 -0.0362 1.0000 0.0662
-6.500 -0.6272 0.04166 0.03518 -0.0351 1.0000 0.0646
-6.250 -0.6144 0.03845 0.03157 -0.0340 1.0000 0.0634
-6.000 -0.5990 0.03588 0.02855 -0.0330 1.0000 0.0639
-5.750 -0.5813 0.03366 0.02590 -0.0320 1.0000 0.0645
-5.500 -0.5557 0.03142 0.02319 -0.0321 0.9984 0.0649
-5.250 -0.5205 0.02940 0.02075 -0.0337 0.9944 0.0655
-5.000 -0.4864 0.02791 0.01892 -0.0348 0.9899 0.0670
-4.750 -0.4529 0.02609 0.01712 -0.0363 0.9859 0.0705
-4.500 -0.4192 0.02526 0.01622 -0.0377 0.9814 0.0778
-4.250 -0.3885 0.02411 0.01516 -0.0386 0.9762 0.0867
-4.000 -0.3536 0.02295 0.01413 -0.0402 0.9720 0.1098
-3.750 -0.3287 0.02103 0.01314 -0.0408 0.9667 0.2359
-3.500 -0.3002 0.02014 0.01302 -0.0418 0.9612 0.3908
-3.250 -0.2715 0.01991 0.01350 -0.0420 0.9559 0.5386
-3.000 -0.2486 0.02008 0.01384 -0.0407 0.9487 0.6218
-2.750 -0.2150 0.02052 0.01429 -0.0411 0.9434 0.6836
-2.500 -0.1971 0.02073 0.01453 -0.0386 0.9355 0.7229
-2.250 -0.1661 0.02107 0.01483 -0.0384 0.9296 0.7630
-2.000 -0.1486 0.02125 0.01499 -0.0358 0.9215 0.7945
-1.750 -0.1198 0.02147 0.01516 -0.0351 0.9152 0.8270
-1.500 -0.1026 0.02161 0.01527 -0.0324 0.9069 0.8567
-1.250 -0.0714 0.02176 0.01536 -0.0321 0.9005 0.8874
-1.000 -0.0431 0.02194 0.01546 -0.0318 0.8927 0.9169
-0.750 0.0109 0.02218 0.01559 -0.0364 0.8871 0.9435
-0.500 0.0886 0.02244 0.01568 -0.0457 0.8842 0.9606
-0.250 0.1559 0.02264 0.01576 -0.0537 0.8778 0.9752
0.000 0.2319 0.02260 0.01559 -0.0632 0.8733 0.9865
0.250 0.3121 0.02230 0.01521 -0.0733 0.8704 0.9951
0.500 0.3481 0.02222 0.01508 -0.0759 0.8607 1.0000
0.750 0.3959 0.02182 0.01464 -0.0798 0.8549 1.0000
1.000 0.4024 0.02185 0.01465 -0.0768 0.8421 1.0000
1.250 0.4553 0.02129 0.01405 -0.0810 0.8377 1.0000
1.500 0.4582 0.02136 0.01410 -0.0771 0.8243 1.0000
1.750 0.4648 0.02144 0.01415 -0.0737 0.8113 1.0000
2.000 0.4831 0.02145 0.01413 -0.0721 0.8000 1.0000
2.250 0.5280 0.02093 0.01360 -0.0744 0.7937 1.0000
2.500 0.5469 0.02097 0.01363 -0.0727 0.7812 1.0000
2.750 0.5739 0.02085 0.01351 -0.0722 0.7701 1.0000
3.000 0.6164 0.02025 0.01291 -0.0737 0.7629 1.0000
3.250 0.6398 0.02020 0.01288 -0.0725 0.7499 1.0000
3.500 0.6663 0.02005 0.01275 -0.0718 0.7373 1.0000
3.750 0.6958 0.01979 0.01250 -0.0714 0.7253 1.0000
4.000 0.7287 0.01938 0.01212 -0.0713 0.7137 1.0000
4.250 0.7626 0.01891 0.01166 -0.0714 0.7016 1.0000
4.500 0.7901 0.01866 0.01142 -0.0706 0.6866 1.0000
4.750 0.8143 0.01851 0.01131 -0.0694 0.6696 1.0000
5.000 0.8387 0.01837 0.01121 -0.0682 0.6515 1.0000
5.250 0.8650 0.01815 0.01101 -0.0672 0.6328 1.0000
5.500 0.8932 0.01790 0.01074 -0.0665 0.6136 1.0000
5.750 0.9164 0.01789 0.01075 -0.0652 0.5910 1.0000
6.000 0.9430 0.01783 0.01061 -0.0643 0.5682 1.0000
6.250 0.9645 0.01801 0.01077 -0.0628 0.5423 1.0000
6.500 0.9865 0.01828 0.01099 -0.0614 0.5158 1.0000
6.750 1.0078 0.01863 0.01125 -0.0600 0.4889 1.0000
7.000 1.0282 0.01907 0.01158 -0.0584 0.4617 1.0000
7.250 1.0466 0.01959 0.01203 -0.0567 0.4341 1.0000
7.500 1.0635 0.02017 0.01257 -0.0548 0.4063 1.0000
7.750 1.0798 0.02081 0.01315 -0.0528 0.3792 1.0000
8.000 1.0952 0.02151 0.01376 -0.0508 0.3526 1.0000
8.250 1.1102 0.02228 0.01440 -0.0488 0.3271 1.0000
8.500 1.1230 0.02307 0.01516 -0.0464 0.3016 1.0000
8.750 1.1354 0.02395 0.01601 -0.0442 0.2776 1.0000
9.000 1.1472 0.02488 0.01682 -0.0419 0.2552 1.0000
9.250 1.1574 0.02587 0.01781 -0.0394 0.2333 1.0000
9.500 1.1667 0.02691 0.01877 -0.0368 0.2135 1.0000
9.750 1.1757 0.02807 0.01983 -0.0343 0.1951 1.0000
10.000 1.1823 0.02923 0.02103 -0.0315 0.1776 1.0000
10.250 1.1879 0.03048 0.02228 -0.0288 0.1610 1.0000
10.500 1.1903 0.03173 0.02353 -0.0259 0.1454 1.0000
10.750 1.1907 0.03306 0.02487 -0.0231 0.1307 1.0000
11.000 1.1904 0.03455 0.02637 -0.0206 0.1169 1.0000
11.250 1.1908 0.03630 0.02813 -0.0183 0.1037 1.0000
11.500 1.1904 0.03829 0.03014 -0.0162 0.0910 1.0000
11.750 1.1894 0.04056 0.03242 -0.0143 0.0790 1.0000
12.000 1.1902 0.04303 0.03491 -0.0126 0.0689 1.0000
12.250 1.1955 0.04566 0.03750 -0.0111 0.0607 1.0000
12.500 1.2006 0.04805 0.03998 -0.0098 0.0549 1.0000
12.750 1.2106 0.05081 0.04280 -0.0088 0.0503 1.0000
13.000 1.2142 0.05345 0.04571 -0.0077 0.0473 1.0000
13.250 1.2195 0.05597 0.04834 -0.0069 0.0448 1.0000
13.500 1.2386 0.05958 0.05191 -0.0064 0.0423 1.0000
13.750 1.2328 0.06304 0.05571 -0.0054 0.0417 1.0000
14.000 1.2245 0.06693 0.05993 -0.0048 0.0413 1.0000
14.250 1.2127 0.07125 0.06457 -0.0046 0.0409 1.0000
14.500 1.1986 0.07594 0.06955 -0.0049 0.0408 1.0000
14.750 1.1813 0.08116 0.07506 -0.0058 0.0408 1.0000
15.000 1.1619 0.08687 0.08102 -0.0075 0.0408 1.0000
15.250 1.1413 0.09310 0.08750 -0.0099 0.0410 1.0000
15.500 1.1169 0.10032 0.09495 -0.0134 0.0412 1.0000
15.750 1.0942 0.10794 0.10276 -0.0175 0.0415 1.0000
16.000 1.0702 0.11641 0.11141 -0.0225 0.0418 1.0000
16.250 1.0464 0.12563 0.12076 -0.0281 0.0422 1.0000
16.500 0.8946 0.17975 0.17491 -0.0621 0.0605 1.0000
16.750 0.8952 0.18595 0.18109 -0.0650 0.0612 1.0000
17.000 0.9000 0.19109 0.18623 -0.0670 0.0621 1.0000
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Polar data table (+)
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