PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU-90-125WL (psu-90-125wl-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.7 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu-90-125wl-il-1000000.txt Download as CSV file: xf-psu-90-125wl-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7718 0.03842 0.03565 -0.0784 1.0000 0.0103
-11.500 -0.7962 0.03620 0.03328 -0.0748 1.0000 0.0102
-11.250 -0.8163 0.03479 0.03179 -0.0697 0.9995 0.0103
-11.000 -0.7990 0.03132 0.02805 -0.0730 0.9956 0.0104
-10.750 -0.7751 0.02963 0.02626 -0.0751 0.9925 0.0106
-10.500 -0.7523 0.02766 0.02412 -0.0768 0.9884 0.0108
-10.250 -0.7265 0.02566 0.02193 -0.0788 0.9855 0.0110
-10.000 -0.6963 0.02442 0.02059 -0.0809 0.9836 0.0113
-9.750 -0.6733 0.02307 0.01908 -0.0813 0.9770 0.0117
-9.500 -0.6447 0.02155 0.01737 -0.0828 0.9728 0.0121
-9.250 -0.6203 0.02012 0.01576 -0.0832 0.9640 0.0122
-9.000 -0.5914 0.01887 0.01434 -0.0842 0.9564 0.0124
-8.750 -0.5650 0.01776 0.01308 -0.0846 0.9444 0.0126
-8.500 -0.5385 0.01708 0.01227 -0.0848 0.9308 0.0128
-8.250 -0.5141 0.01639 0.01143 -0.0844 0.9163 0.0129
-8.000 -0.4912 0.01565 0.01055 -0.0838 0.9024 0.0130
-7.750 -0.4733 0.01405 0.00879 -0.0824 0.8892 0.0134
-7.500 -0.4524 0.01319 0.00783 -0.0815 0.8784 0.0137
-7.250 -0.4296 0.01261 0.00717 -0.0808 0.8689 0.0141
-7.000 -0.4054 0.01219 0.00670 -0.0803 0.8603 0.0147
-6.750 -0.3811 0.01177 0.00619 -0.0798 0.8526 0.0151
-6.500 -0.3565 0.01134 0.00570 -0.0793 0.8451 0.0155
-6.000 -0.3060 0.01062 0.00484 -0.0785 0.8317 0.0163
-5.750 -0.2803 0.01032 0.00446 -0.0782 0.8254 0.0167
-5.500 -0.2542 0.01001 0.00409 -0.0779 0.8197 0.0170
-5.250 -0.2288 0.00957 0.00358 -0.0775 0.8138 0.0179
-5.000 -0.2026 0.00929 0.00324 -0.0773 0.8084 0.0192
-4.750 -0.1757 0.00906 0.00298 -0.0771 0.8032 0.0206
-4.500 -0.1486 0.00886 0.00273 -0.0770 0.7978 0.0224
-4.250 -0.1221 0.00860 0.00248 -0.0767 0.7927 0.0310
-4.000 -0.0970 0.00806 0.00220 -0.0765 0.7878 0.0857
-3.750 -0.0708 0.00772 0.00202 -0.0764 0.7827 0.1305
-3.500 -0.0445 0.00743 0.00186 -0.0762 0.7779 0.1781
-3.250 -0.0179 0.00712 0.00174 -0.0762 0.7732 0.2284
-3.000 0.0088 0.00683 0.00162 -0.0761 0.7684 0.2819
-2.750 0.0355 0.00658 0.00152 -0.0761 0.7637 0.3374
-2.500 0.0624 0.00632 0.00144 -0.0760 0.7590 0.3962
-2.250 0.0896 0.00611 0.00137 -0.0760 0.7540 0.4449
-2.000 0.1162 0.00587 0.00131 -0.0758 0.7490 0.5120
-1.750 0.1433 0.00571 0.00131 -0.0757 0.7440 0.5693
-1.500 0.1712 0.00564 0.00129 -0.0757 0.7387 0.5971
-1.250 0.1992 0.00562 0.00128 -0.0757 0.7335 0.6167
-1.000 0.2275 0.00560 0.00128 -0.0757 0.7284 0.6341
-0.750 0.2557 0.00558 0.00127 -0.0758 0.7228 0.6494
-0.500 0.2836 0.00559 0.00126 -0.0757 0.7170 0.6628
-0.250 0.3119 0.00556 0.00127 -0.0758 0.7110 0.6751
0.000 0.3399 0.00557 0.00127 -0.0758 0.7043 0.6865
0.250 0.3680 0.00557 0.00128 -0.0758 0.6977 0.6979
0.500 0.3959 0.00557 0.00129 -0.0757 0.6903 0.7085
0.750 0.4239 0.00558 0.00130 -0.0757 0.6828 0.7184
1.000 0.4517 0.00560 0.00132 -0.0757 0.6741 0.7284
1.250 0.4795 0.00560 0.00134 -0.0756 0.6650 0.7382
1.500 0.5069 0.00563 0.00137 -0.0755 0.6545 0.7485
1.750 0.5341 0.00568 0.00140 -0.0753 0.6418 0.7593
2.000 0.5610 0.00572 0.00143 -0.0751 0.6271 0.7696
2.250 0.5877 0.00578 0.00149 -0.0748 0.6107 0.7803
2.500 0.6141 0.00587 0.00154 -0.0745 0.5919 0.7919
2.750 0.6397 0.00598 0.00162 -0.0741 0.5707 0.8041
3.000 0.6650 0.00611 0.00172 -0.0736 0.5494 0.8169
3.250 0.6901 0.00625 0.00183 -0.0730 0.5273 0.8305
3.500 0.7147 0.00642 0.00195 -0.0724 0.5045 0.8454
3.750 0.7391 0.00657 0.00209 -0.0717 0.4821 0.8621
4.000 0.7627 0.00674 0.00223 -0.0708 0.4601 0.8812
4.250 0.7855 0.00689 0.00237 -0.0698 0.4381 0.9029
4.500 0.8068 0.00705 0.00252 -0.0684 0.4173 0.9304
4.750 0.8324 0.00723 0.00268 -0.0680 0.3942 0.9632
5.000 0.8689 0.00751 0.00286 -0.0701 0.3694 0.9908
5.250 0.8956 0.00779 0.00304 -0.0702 0.3460 1.0000
5.500 0.9191 0.00807 0.00324 -0.0695 0.3244 1.0000
5.750 0.9425 0.00837 0.00344 -0.0688 0.3024 1.0000
6.000 0.9653 0.00870 0.00367 -0.0680 0.2791 1.0000
6.250 0.9874 0.00907 0.00392 -0.0672 0.2540 1.0000
6.500 1.0097 0.00943 0.00418 -0.0663 0.2301 1.0000
6.750 1.0312 0.00984 0.00447 -0.0653 0.2058 1.0000
7.000 1.0525 0.01025 0.00477 -0.0644 0.1839 1.0000
7.250 1.0740 0.01064 0.00507 -0.0634 0.1652 1.0000
7.500 1.0947 0.01107 0.00541 -0.0623 0.1453 1.0000
7.750 1.1145 0.01154 0.00577 -0.0611 0.1261 1.0000
8.000 1.1350 0.01195 0.00612 -0.0600 0.1118 1.0000
8.250 1.1544 0.01241 0.00650 -0.0587 0.0962 1.0000
8.500 1.1730 0.01290 0.00692 -0.0573 0.0816 1.0000
8.750 1.1908 0.01339 0.00734 -0.0558 0.0689 1.0000
9.000 1.2063 0.01390 0.00778 -0.0538 0.0571 1.0000
9.250 1.2206 0.01444 0.00826 -0.0516 0.0465 1.0000
9.500 1.2329 0.01509 0.00883 -0.0492 0.0349 1.0000
9.750 1.2420 0.01594 0.00958 -0.0464 0.0208 1.0000
10.000 1.2507 0.01684 0.01042 -0.0435 0.0115 1.0000
10.250 1.2645 0.01746 0.01106 -0.0416 0.0102 1.0000
10.500 1.2773 0.01817 0.01180 -0.0395 0.0090 1.0000
10.750 1.2907 0.01884 0.01254 -0.0377 0.0084 1.0000
11.000 1.3036 0.01956 0.01331 -0.0358 0.0081 1.0000
11.250 1.3145 0.02042 0.01422 -0.0338 0.0075 1.0000
11.500 1.3230 0.02147 0.01534 -0.0316 0.0071 1.0000
11.750 1.3298 0.02267 0.01663 -0.0294 0.0069 1.0000
12.000 1.3404 0.02363 0.01766 -0.0277 0.0068 1.0000
12.250 1.3504 0.02468 0.01877 -0.0261 0.0066 1.0000
12.500 1.3590 0.02586 0.02002 -0.0245 0.0064 1.0000
12.750 1.3662 0.02718 0.02142 -0.0228 0.0062 1.0000
13.000 1.3736 0.02853 0.02284 -0.0214 0.0060 1.0000
13.250 1.3795 0.03004 0.02443 -0.0199 0.0059 1.0000
13.500 1.3857 0.03158 0.02604 -0.0187 0.0056 1.0000
13.750 1.3885 0.03346 0.02800 -0.0174 0.0055 1.0000
14.000 1.3899 0.03553 0.03016 -0.0162 0.0054 1.0000
14.250 1.3903 0.03780 0.03252 -0.0151 0.0054 1.0000
14.500 1.3892 0.04029 0.03511 -0.0143 0.0053 1.0000
14.750 1.3841 0.04331 0.03824 -0.0136 0.0052 1.0000
15.000 1.3792 0.04649 0.04153 -0.0132 0.0051 1.0000
15.250 1.3764 0.04958 0.04472 -0.0131 0.0051 1.0000
15.500 1.3532 0.05535 0.05067 -0.0135 0.0050 1.0000
15.750 1.3515 0.05874 0.05415 -0.0141 0.0050 1.0000
16.000 1.3491 0.06236 0.05787 -0.0149 0.0050 1.0000
16.250 1.3359 0.06765 0.06330 -0.0163 0.0049 1.0000
16.500 1.3301 0.07210 0.06785 -0.0178 0.0049 1.0000
16.750 1.3261 0.07644 0.07230 -0.0194 0.0049 1.0000
17.000 1.3184 0.08146 0.07744 -0.0213 0.0048 1.0000
17.250 1.3088 0.08691 0.08300 -0.0236 0.0049 1.0000
17.500 1.3026 0.09199 0.08820 -0.0259 0.0049 1.0000
17.750 1.2924 0.09784 0.09416 -0.0285 0.0048 1.0000
18.000 1.2870 0.10304 0.09947 -0.0311 0.0048 1.0000
18.250 1.2761 0.10922 0.10576 -0.0342 0.0048 1.0000
18.500 1.2663 0.11529 0.11195 -0.0373 0.0048 1.0000
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Polar data table (+)
Polar graphs
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