PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: PSU-90-125WL (psu-90-125wl-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-psu-90-125wl-il-1000000-n5.txt Download as CSV file: xf-psu-90-125wl-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7452 0.08076 0.07860 -0.0532 1.0000 0.0072
-14.500 -0.7835 0.06923 0.06692 -0.0603 1.0000 0.0072
-14.250 -0.8217 0.05813 0.05562 -0.0679 1.0000 0.0071
-14.000 -0.8419 0.05094 0.04828 -0.0730 1.0000 0.0071
-13.750 -0.8548 0.04563 0.04282 -0.0765 1.0000 0.0071
-13.500 -0.8682 0.04096 0.03800 -0.0791 1.0000 0.0072
-13.250 -0.8755 0.03761 0.03453 -0.0803 1.0000 0.0072
-13.000 -0.8826 0.03479 0.03159 -0.0806 1.0000 0.0073
-12.750 -0.8853 0.03283 0.02954 -0.0799 1.0000 0.0073
-12.500 -0.8956 0.03080 0.02739 -0.0779 1.0000 0.0074
-12.000 -0.8769 0.02757 0.02391 -0.0783 0.9935 0.0075
-11.750 -0.8607 0.02591 0.02209 -0.0789 0.9878 0.0076
-11.250 -0.8159 0.02354 0.01946 -0.0806 0.9779 0.0077
-11.000 -0.7902 0.02232 0.01811 -0.0819 0.9721 0.0077
-10.750 -0.7661 0.02110 0.01675 -0.0827 0.9628 0.0078
-10.500 -0.7439 0.01910 0.01455 -0.0837 0.9497 0.0080
-10.250 -0.7179 0.01797 0.01328 -0.0845 0.9339 0.0082
-10.000 -0.6946 0.01719 0.01235 -0.0844 0.9155 0.0083
-9.750 -0.6738 0.01655 0.01157 -0.0837 0.8982 0.0084
-9.500 -0.6528 0.01600 0.01091 -0.0828 0.8834 0.0086
-9.250 -0.6316 0.01545 0.01024 -0.0820 0.8706 0.0087
-9.000 -0.6094 0.01496 0.00966 -0.0813 0.8601 0.0089
-8.750 -0.5868 0.01448 0.00909 -0.0807 0.8512 0.0090
-8.500 -0.5636 0.01404 0.00856 -0.0801 0.8425 0.0092
-8.250 -0.5398 0.01363 0.00808 -0.0796 0.8348 0.0095
-8.000 -0.5157 0.01325 0.00762 -0.0791 0.8271 0.0098
-7.750 -0.4916 0.01283 0.00712 -0.0786 0.8207 0.0100
-7.500 -0.4671 0.01242 0.00663 -0.0782 0.8143 0.0102
-7.250 -0.4423 0.01206 0.00619 -0.0778 0.8085 0.0104
-7.000 -0.4169 0.01171 0.00580 -0.0775 0.8026 0.0106
-6.750 -0.3914 0.01141 0.00542 -0.0772 0.7970 0.0108
-6.500 -0.3656 0.01111 0.00508 -0.0770 0.7919 0.0109
-6.250 -0.3394 0.01085 0.00476 -0.0768 0.7863 0.0110
-6.000 -0.3144 0.01044 0.00426 -0.0764 0.7808 0.0114
-5.750 -0.2882 0.01011 0.00389 -0.0761 0.7758 0.0118
-5.500 -0.2618 0.00984 0.00358 -0.0760 0.7706 0.0122
-5.250 -0.2352 0.00963 0.00332 -0.0758 0.7658 0.0127
-5.000 -0.2081 0.00941 0.00308 -0.0757 0.7612 0.0132
-4.750 -0.1810 0.00923 0.00286 -0.0756 0.7561 0.0138
-4.500 -0.1539 0.00908 0.00267 -0.0755 0.7513 0.0146
-4.250 -0.1263 0.00893 0.00250 -0.0755 0.7468 0.0151
-4.000 -0.0989 0.00876 0.00230 -0.0754 0.7417 0.0169
-3.750 -0.0717 0.00861 0.00213 -0.0753 0.7369 0.0197
-3.500 -0.0449 0.00833 0.00195 -0.0752 0.7324 0.0427
-3.250 -0.0180 0.00807 0.00179 -0.0752 0.7274 0.0704
-3.000 0.0088 0.00783 0.00165 -0.0751 0.7226 0.1030
-2.750 0.0358 0.00759 0.00153 -0.0751 0.7180 0.1405
-2.500 0.0628 0.00733 0.00142 -0.0751 0.7127 0.1837
-2.250 0.0896 0.00709 0.00132 -0.0750 0.7073 0.2336
-2.000 0.1170 0.00691 0.00124 -0.0750 0.7018 0.2716
-1.750 0.1439 0.00667 0.00117 -0.0750 0.6954 0.3260
-1.500 0.1705 0.00640 0.00111 -0.0750 0.6895 0.3962
-1.250 0.1977 0.00620 0.00106 -0.0750 0.6829 0.4493
-1.000 0.2249 0.00607 0.00103 -0.0749 0.6763 0.4932
-0.750 0.2526 0.00596 0.00102 -0.0749 0.6689 0.5304
-0.500 0.2801 0.00591 0.00102 -0.0748 0.6607 0.5603
-0.250 0.3079 0.00588 0.00102 -0.0748 0.6506 0.5832
0.000 0.3355 0.00588 0.00103 -0.0748 0.6395 0.6025
0.250 0.3629 0.00590 0.00104 -0.0747 0.6264 0.6189
0.500 0.3902 0.00594 0.00107 -0.0745 0.6118 0.6326
0.750 0.4173 0.00601 0.00109 -0.0744 0.5949 0.6446
1.000 0.4441 0.00610 0.00114 -0.0742 0.5763 0.6558
1.250 0.4706 0.00620 0.00119 -0.0739 0.5569 0.6662
1.500 0.4970 0.00633 0.00126 -0.0737 0.5359 0.6768
1.750 0.5231 0.00647 0.00134 -0.0734 0.5149 0.6876
2.000 0.5494 0.00660 0.00142 -0.0731 0.4943 0.6978
2.250 0.5754 0.00676 0.00152 -0.0728 0.4731 0.7074
2.500 0.6015 0.00691 0.00162 -0.0725 0.4535 0.7175
2.750 0.6274 0.00705 0.00173 -0.0721 0.4337 0.7279
3.000 0.6531 0.00722 0.00185 -0.0718 0.4142 0.7383
3.250 0.6788 0.00739 0.00198 -0.0714 0.3946 0.7488
3.500 0.7042 0.00757 0.00211 -0.0710 0.3741 0.7598
3.750 0.7291 0.00777 0.00226 -0.0706 0.3535 0.7712
4.000 0.7543 0.00795 0.00241 -0.0701 0.3350 0.7833
4.250 0.7793 0.00814 0.00257 -0.0697 0.3167 0.7959
4.750 0.8280 0.00856 0.00293 -0.0685 0.2799 0.8223
5.000 0.8522 0.00876 0.00311 -0.0679 0.2630 0.8369
5.500 0.8983 0.00919 0.00352 -0.0662 0.2276 0.8726
5.750 0.9194 0.00946 0.00377 -0.0650 0.2080 0.8963
6.000 0.9386 0.00972 0.00402 -0.0633 0.1850 0.9299
6.250 0.9672 0.01013 0.00433 -0.0638 0.1573 0.9794
6.500 0.9925 0.01049 0.00460 -0.0637 0.1408 1.0000
6.750 1.0143 0.01087 0.00489 -0.0628 0.1236 1.0000
7.000 1.0353 0.01130 0.00523 -0.0618 0.1045 1.0000
7.250 1.0558 0.01174 0.00558 -0.0607 0.0881 1.0000
7.500 1.0770 0.01213 0.00591 -0.0597 0.0763 1.0000
7.750 1.0977 0.01252 0.00625 -0.0586 0.0655 1.0000
8.000 1.1176 0.01295 0.00663 -0.0574 0.0547 1.0000
8.250 1.1352 0.01350 0.00709 -0.0558 0.0414 1.0000
8.750 1.1680 0.01449 0.00798 -0.0522 0.0242 1.0000
9.000 1.1799 0.01516 0.00858 -0.0497 0.0130 1.0000
9.250 1.1932 0.01579 0.00918 -0.0474 0.0076 1.0000
9.500 1.2099 0.01624 0.00966 -0.0458 0.0068 1.0000
9.750 1.2254 0.01676 0.01020 -0.0440 0.0060 1.0000
10.000 1.2407 0.01730 0.01078 -0.0422 0.0054 1.0000
10.250 1.2561 0.01785 0.01136 -0.0405 0.0051 1.0000
10.500 1.2715 0.01839 0.01195 -0.0389 0.0050 1.0000
10.750 1.2858 0.01901 0.01262 -0.0372 0.0048 1.0000
11.000 1.2995 0.01968 0.01334 -0.0355 0.0046 1.0000
11.250 1.3130 0.02038 0.01409 -0.0338 0.0044 1.0000
11.500 1.3254 0.02116 0.01493 -0.0321 0.0043 1.0000
11.750 1.3375 0.02198 0.01580 -0.0305 0.0041 1.0000
12.000 1.3481 0.02294 0.01681 -0.0288 0.0039 1.0000
12.250 1.3580 0.02396 0.01789 -0.0271 0.0038 1.0000
12.500 1.3676 0.02505 0.01904 -0.0255 0.0037 1.0000
12.750 1.3749 0.02634 0.02041 -0.0238 0.0036 1.0000
13.000 1.3817 0.02770 0.02186 -0.0223 0.0034 1.0000
13.250 1.3878 0.02917 0.02341 -0.0207 0.0034 1.0000
13.500 1.3982 0.03034 0.02463 -0.0197 0.0033 1.0000
13.750 1.4047 0.03186 0.02624 -0.0185 0.0033 1.0000
14.000 1.4122 0.03334 0.02779 -0.0175 0.0032 1.0000
14.250 1.4158 0.03521 0.02975 -0.0164 0.0032 1.0000
14.500 1.4194 0.03716 0.03178 -0.0154 0.0031 1.0000
14.750 1.4239 0.03907 0.03377 -0.0147 0.0030 1.0000
15.000 1.4259 0.04130 0.03609 -0.0140 0.0030 1.0000
15.250 1.4258 0.04385 0.03874 -0.0135 0.0030 1.0000
15.500 1.4271 0.04636 0.04134 -0.0132 0.0029 1.0000
15.750 1.4253 0.04933 0.04442 -0.0131 0.0029 1.0000
16.000 1.4237 0.05241 0.04760 -0.0133 0.0028 1.0000
16.250 1.4226 0.05559 0.05087 -0.0136 0.0028 1.0000
16.500 1.4172 0.05947 0.05487 -0.0144 0.0028 1.0000
16.750 1.4136 0.06325 0.05875 -0.0153 0.0027 1.0000
17.000 1.4071 0.06763 0.06325 -0.0166 0.0027 1.0000
17.250 1.3987 0.07248 0.06822 -0.0183 0.0027 1.0000
17.500 1.3877 0.07790 0.07377 -0.0203 0.0027 1.0000
17.750 1.3774 0.08342 0.07941 -0.0226 0.0027 1.0000
18.000 1.3674 0.08907 0.08518 -0.0252 0.0026 1.0000
18.250 1.3549 0.09528 0.09151 -0.0281 0.0026 1.0000
18.500 1.3402 0.10207 0.09843 -0.0314 0.0026 1.0000
18.750 1.3237 0.10939 0.10589 -0.0351 0.0026 1.0000
19.000 1.3091 0.11647 0.11309 -0.0389 0.0026 1.0000
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Polar data table (+)
Polar graphs
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