PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: PSU-90-125WL (psu-90-125wl-il) Reynolds number: 100,000 Max Cl/Cd: 53.25 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-psu-90-125wl-il-100000-n5.txt Download as CSV file: xf-psu-90-125wl-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4388 0.09298 0.08782 -0.0492 1.0000 0.0297
-10.500 -0.4532 0.08579 0.08072 -0.0525 1.0000 0.0291
-10.250 -0.5305 0.06516 0.06000 -0.0672 1.0000 0.0272
-10.000 -0.5723 0.05922 0.05392 -0.0695 1.0000 0.0267
-9.750 -0.6040 0.05662 0.05123 -0.0667 1.0000 0.0265
-9.500 -0.6283 0.05436 0.04887 -0.0629 1.0000 0.0264
-9.250 -0.6478 0.05234 0.04669 -0.0589 1.0000 0.0263
-8.750 -0.6554 0.04605 0.03983 -0.0568 0.9934 0.0263
-8.500 -0.6391 0.04208 0.03540 -0.0588 0.9859 0.0265
-8.250 -0.6194 0.03883 0.03177 -0.0603 0.9790 0.0268
-8.000 -0.5963 0.03610 0.02871 -0.0616 0.9728 0.0272
-7.750 -0.5730 0.03383 0.02614 -0.0624 0.9667 0.0277
-7.500 -0.5471 0.03201 0.02407 -0.0633 0.9607 0.0286
-7.250 -0.5168 0.03038 0.02218 -0.0649 0.9567 0.0304
-7.000 -0.4933 0.02891 0.02043 -0.0648 0.9495 0.0318
-6.750 -0.4632 0.02731 0.01857 -0.0657 0.9453 0.0328
-6.500 -0.4332 0.02594 0.01701 -0.0665 0.9412 0.0336
-6.250 -0.4087 0.02465 0.01565 -0.0664 0.9349 0.0347
-6.000 -0.3785 0.02350 0.01446 -0.0675 0.9309 0.0365
-5.750 -0.3498 0.02257 0.01341 -0.0682 0.9264 0.0388
-5.500 -0.3245 0.02182 0.01253 -0.0680 0.9201 0.0423
-5.250 -0.2944 0.02092 0.01161 -0.0690 0.9160 0.0489
-5.000 -0.2677 0.02009 0.01076 -0.0692 0.9108 0.0596
-4.750 -0.2427 0.01922 0.01000 -0.0691 0.9048 0.0869
-4.500 -0.2127 0.01840 0.00940 -0.0700 0.9009 0.1409
-4.250 -0.1889 0.01764 0.00906 -0.0700 0.8950 0.2245
-4.000 -0.1647 0.01691 0.00879 -0.0699 0.8893 0.3207
-3.750 -0.1353 0.01635 0.00851 -0.0704 0.8854 0.4047
-3.500 -0.1127 0.01607 0.00844 -0.0695 0.8789 0.4694
-3.250 -0.0860 0.01587 0.00840 -0.0690 0.8737 0.5306
-3.000 -0.0548 0.01574 0.00830 -0.0693 0.8700 0.5818
-2.750 -0.0327 0.01578 0.00833 -0.0679 0.8628 0.6175
-2.500 -0.0042 0.01575 0.00826 -0.0676 0.8578 0.6501
-2.250 0.0260 0.01570 0.00816 -0.0677 0.8537 0.6780
-2.000 0.0481 0.01577 0.00818 -0.0663 0.8461 0.7018
-1.750 0.0777 0.01572 0.00810 -0.0662 0.8414 0.7234
-1.500 0.1021 0.01575 0.00809 -0.0652 0.8349 0.7431
-1.250 0.1288 0.01574 0.00802 -0.0646 0.8287 0.7618
-1.000 0.1596 0.01566 0.00789 -0.0647 0.8244 0.7792
-0.750 0.1806 0.01573 0.00796 -0.0631 0.8160 0.7954
-0.500 0.2102 0.01565 0.00783 -0.0630 0.8110 0.8114
-0.250 0.2326 0.01570 0.00787 -0.0617 0.8030 0.8272
0.000 0.2611 0.01563 0.00777 -0.0613 0.7971 0.8427
0.250 0.2856 0.01563 0.00777 -0.0604 0.7894 0.8583
0.500 0.3142 0.01557 0.00769 -0.0601 0.7827 0.8737
0.750 0.3414 0.01555 0.00767 -0.0597 0.7749 0.8896
1.000 0.3732 0.01547 0.00758 -0.0602 0.7676 0.9048
1.250 0.4047 0.01546 0.00757 -0.0607 0.7590 0.9205
1.500 0.4424 0.01536 0.00746 -0.0624 0.7516 0.9346
1.750 0.4781 0.01536 0.00747 -0.0641 0.7417 0.9497
2.000 0.5184 0.01527 0.00737 -0.0665 0.7333 0.9632
2.250 0.5575 0.01522 0.00734 -0.0689 0.7229 0.9776
2.500 0.5965 0.01518 0.00732 -0.0713 0.7112 0.9931
2.750 0.6211 0.01518 0.00731 -0.0710 0.6996 1.0000
3.000 0.6402 0.01519 0.00731 -0.0694 0.6879 1.0000
3.250 0.6618 0.01521 0.00730 -0.0682 0.6756 1.0000
3.500 0.6836 0.01526 0.00734 -0.0670 0.6620 1.0000
3.750 0.7059 0.01532 0.00739 -0.0660 0.6471 1.0000
4.000 0.7280 0.01541 0.00750 -0.0649 0.6307 1.0000
4.250 0.7507 0.01550 0.00760 -0.0638 0.6131 1.0000
4.500 0.7741 0.01560 0.00767 -0.0629 0.5945 1.0000
4.750 0.7981 0.01570 0.00773 -0.0620 0.5752 1.0000
5.000 0.8209 0.01588 0.00790 -0.0610 0.5539 1.0000
5.250 0.8440 0.01610 0.00805 -0.0600 0.5322 1.0000
5.500 0.8660 0.01637 0.00828 -0.0589 0.5093 1.0000
5.750 0.8878 0.01669 0.00852 -0.0577 0.4864 1.0000
6.000 0.9084 0.01706 0.00887 -0.0565 0.4625 1.0000
6.250 0.9287 0.01747 0.00922 -0.0552 0.4390 1.0000
6.500 0.9482 0.01792 0.00962 -0.0538 0.4153 1.0000
6.750 0.9671 0.01841 0.01006 -0.0524 0.3919 1.0000
7.000 0.9852 0.01894 0.01053 -0.0508 0.3691 1.0000
7.250 1.0029 0.01948 0.01108 -0.0493 0.3459 1.0000
7.500 1.0194 0.02009 0.01162 -0.0476 0.3241 1.0000
7.750 1.0356 0.02070 0.01223 -0.0459 0.3018 1.0000
8.000 1.0504 0.02139 0.01286 -0.0440 0.2809 1.0000
8.250 1.0649 0.02208 0.01355 -0.0422 0.2599 1.0000
8.500 1.0771 0.02281 0.01427 -0.0400 0.2406 1.0000
8.750 1.0882 0.02361 0.01504 -0.0377 0.2227 1.0000
9.000 1.1000 0.02443 0.01588 -0.0356 0.2048 1.0000
9.250 1.1110 0.02532 0.01677 -0.0335 0.1881 1.0000
9.500 1.1213 0.02629 0.01775 -0.0314 0.1722 1.0000
9.750 1.1311 0.02733 0.01880 -0.0294 0.1577 1.0000
10.000 1.1404 0.02844 0.01993 -0.0275 0.1441 1.0000
10.250 1.1491 0.02963 0.02119 -0.0256 0.1318 1.0000
10.500 1.1566 0.03092 0.02251 -0.0238 0.1192 1.0000
10.750 1.1630 0.03233 0.02391 -0.0221 0.1048 1.0000
11.000 1.1684 0.03386 0.02542 -0.0206 0.0902 1.0000
11.250 1.1731 0.03552 0.02705 -0.0191 0.0763 1.0000
11.500 1.1776 0.03728 0.02882 -0.0178 0.0650 1.0000
11.750 1.1813 0.03918 0.03079 -0.0165 0.0564 1.0000
12.000 1.1822 0.04140 0.03303 -0.0152 0.0489 1.0000
12.250 1.1825 0.04375 0.03548 -0.0142 0.0428 1.0000
12.500 1.1805 0.04643 0.03827 -0.0132 0.0382 1.0000
12.750 1.1779 0.04927 0.04123 -0.0125 0.0342 1.0000
13.000 1.1713 0.05264 0.04463 -0.0120 0.0316 1.0000
13.250 1.1680 0.05582 0.04801 -0.0117 0.0286 1.0000
13.500 1.1636 0.05926 0.05158 -0.0118 0.0266 1.0000
13.750 1.1569 0.06311 0.05553 -0.0123 0.0252 1.0000
14.000 1.1490 0.06731 0.05982 -0.0131 0.0242 1.0000
14.250 1.1444 0.07130 0.06402 -0.0139 0.0230 1.0000
14.500 1.1387 0.07559 0.06849 -0.0151 0.0220 1.0000
14.750 1.1328 0.08007 0.07313 -0.0164 0.0213 1.0000
15.000 1.1264 0.08478 0.07799 -0.0181 0.0207 1.0000
15.250 1.1198 0.08967 0.08302 -0.0199 0.0202 1.0000
15.500 1.1134 0.09466 0.08816 -0.0220 0.0198 1.0000
15.750 1.1067 0.09984 0.09346 -0.0242 0.0195 1.0000
16.000 1.0998 0.10512 0.09887 -0.0266 0.0191 1.0000
16.250 1.0938 0.11031 0.10416 -0.0290 0.0188 1.0000
16.500 1.0882 0.11553 0.10949 -0.0314 0.0186 1.0000
16.750 1.0808 0.12142 0.11557 -0.0344 0.0184 1.0000
17.000 1.0721 0.12776 0.12210 -0.0378 0.0182 1.0000
17.250 1.0622 0.13459 0.12911 -0.0416 0.0181 1.0000
17.500 1.0504 0.14213 0.13682 -0.0460 0.0181 1.0000
17.750 1.0360 0.15068 0.14555 -0.0512 0.0181 1.0000
18.000 1.0207 0.15992 0.15494 -0.0568 0.0182 1.0000
18.250 1.0030 0.17037 0.16552 -0.0631 0.0183 1.0000
18.500 0.9811 0.18307 0.17831 -0.0703 0.0185 1.0000
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Polar data table (+)
Polar graphs
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