PSU-90-125WL (psu-90-125wl-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: PSU-90-125WL (psu-90-125wl-il) Reynolds number: 500,000 Max Cl/Cd: 102.51 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-psu-90-125wl-il-500000.txt Download as CSV file: xf-psu-90-125wl-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4260 0.10750 0.10512 -0.0439 1.0000 0.0275
-11.500 -0.4308 0.10164 0.09929 -0.0468 1.0000 0.0277
-11.250 -0.4481 0.09461 0.09231 -0.0487 1.0000 0.0284
-11.000 -0.4478 0.09138 0.08910 -0.0494 1.0000 0.0287
-10.750 -0.4410 0.09015 0.08788 -0.0489 1.0000 0.0294
-10.500 -0.4425 0.08661 0.08437 -0.0500 1.0000 0.0299
-10.250 -0.4500 0.08168 0.07947 -0.0520 1.0000 0.0303
-10.000 -0.4618 0.07585 0.07368 -0.0548 1.0000 0.0307
-9.000 -0.5972 0.03274 0.02852 -0.0793 0.9745 0.0220
-8.750 -0.5757 0.02687 0.02234 -0.0813 0.9715 0.0196
-8.500 -0.5540 0.02396 0.01905 -0.0816 0.9634 0.0194
-8.250 -0.5252 0.02156 0.01632 -0.0828 0.9589 0.0192
-8.000 -0.4988 0.01995 0.01450 -0.0832 0.9513 0.0193
-7.750 -0.4693 0.01857 0.01296 -0.0840 0.9452 0.0197
-7.500 -0.4418 0.01756 0.01182 -0.0842 0.9372 0.0203
-7.250 -0.4134 0.01656 0.01069 -0.0846 0.9300 0.0208
-7.000 -0.3884 0.01567 0.00969 -0.0843 0.9206 0.0211
-6.750 -0.3620 0.01490 0.00880 -0.0841 0.9131 0.0214
-6.500 -0.3380 0.01432 0.00812 -0.0835 0.9037 0.0217
-6.250 -0.3165 0.01325 0.00696 -0.0826 0.8955 0.0224
-6.000 -0.2936 0.01260 0.00624 -0.0819 0.8873 0.0232
-5.750 -0.2689 0.01213 0.00569 -0.0814 0.8803 0.0242
-5.500 -0.2440 0.01175 0.00526 -0.0809 0.8730 0.0255
-5.250 -0.2180 0.01144 0.00486 -0.0806 0.8669 0.0271
-5.000 -0.1933 0.01100 0.00436 -0.0800 0.8600 0.0297
-4.750 -0.1672 0.01068 0.00399 -0.0797 0.8543 0.0343
-4.500 -0.1433 0.01006 0.00357 -0.0792 0.8482 0.0738
-4.250 -0.1190 0.00952 0.00328 -0.0788 0.8422 0.1375
-4.000 -0.0935 0.00913 0.00307 -0.0786 0.8371 0.1950
-3.750 -0.0685 0.00874 0.00290 -0.0783 0.8311 0.2549
-3.500 -0.0429 0.00839 0.00274 -0.0781 0.8257 0.3177
-3.250 -0.0168 0.00810 0.00261 -0.0779 0.8207 0.3767
-3.000 0.0085 0.00777 0.00251 -0.0776 0.8149 0.4449
-2.750 0.0345 0.00752 0.00244 -0.0773 0.8098 0.5096
-2.500 0.0607 0.00737 0.00244 -0.0769 0.8048 0.5674
-2.250 0.0875 0.00730 0.00244 -0.0766 0.7992 0.6075
-2.000 0.1150 0.00727 0.00242 -0.0765 0.7942 0.6324
-1.750 0.1427 0.00727 0.00241 -0.0763 0.7890 0.6516
-1.500 0.1702 0.00725 0.00239 -0.0761 0.7832 0.6686
-1.250 0.1980 0.00725 0.00237 -0.0760 0.7781 0.6843
-1.000 0.2254 0.00725 0.00237 -0.0758 0.7721 0.6989
-0.750 0.2529 0.00723 0.00236 -0.0756 0.7661 0.7121
-0.500 0.2806 0.00724 0.00236 -0.0755 0.7607 0.7245
-0.250 0.3078 0.00722 0.00237 -0.0752 0.7542 0.7365
0.000 0.3356 0.00723 0.00235 -0.0751 0.7483 0.7480
0.250 0.3629 0.00723 0.00237 -0.0749 0.7417 0.7594
0.500 0.3901 0.00721 0.00236 -0.0746 0.7348 0.7699
0.750 0.4173 0.00721 0.00238 -0.0744 0.7277 0.7808
1.000 0.4444 0.00721 0.00238 -0.0741 0.7200 0.7924
1.250 0.4713 0.00721 0.00240 -0.0738 0.7123 0.8038
1.500 0.4979 0.00719 0.00241 -0.0735 0.7039 0.8148
1.750 0.5244 0.00719 0.00244 -0.0731 0.6949 0.8266
2.000 0.5507 0.00720 0.00245 -0.0726 0.6857 0.8392
2.250 0.5766 0.00719 0.00248 -0.0721 0.6746 0.8525
2.500 0.6019 0.00718 0.00252 -0.0714 0.6628 0.8664
2.750 0.6266 0.00719 0.00255 -0.0706 0.6498 0.8813
3.000 0.6506 0.00720 0.00260 -0.0697 0.6355 0.8980
3.250 0.6735 0.00722 0.00264 -0.0684 0.6193 0.9169
3.500 0.6969 0.00728 0.00268 -0.0673 0.6006 0.9393
3.750 0.7266 0.00739 0.00275 -0.0676 0.5793 0.9611
4.000 0.7624 0.00758 0.00286 -0.0695 0.5541 0.9801
4.250 0.8006 0.00781 0.00299 -0.0720 0.5274 0.9971
4.500 0.8237 0.00805 0.00313 -0.0713 0.5041 1.0000
4.750 0.8453 0.00831 0.00330 -0.0702 0.4809 1.0000
5.000 0.8674 0.00859 0.00348 -0.0693 0.4571 1.0000
5.500 0.9119 0.00919 0.00392 -0.0674 0.4099 1.0000
5.750 0.9337 0.00953 0.00416 -0.0664 0.3868 1.0000
6.000 0.9556 0.00987 0.00441 -0.0655 0.3621 1.0000
6.250 0.9771 0.01024 0.00469 -0.0645 0.3386 1.0000
6.500 0.9980 0.01064 0.00499 -0.0634 0.3143 1.0000
6.750 1.0192 0.01103 0.00530 -0.0623 0.2910 1.0000
7.000 1.0393 0.01146 0.00564 -0.0612 0.2682 1.0000
7.250 1.0593 0.01191 0.00599 -0.0600 0.2438 1.0000
7.500 1.0783 0.01241 0.00638 -0.0586 0.2189 1.0000
7.750 1.0965 0.01294 0.00680 -0.0572 0.1962 1.0000
8.000 1.1152 0.01342 0.00721 -0.0558 0.1753 1.0000
8.250 1.1319 0.01400 0.00767 -0.0542 0.1544 1.0000
8.500 1.1481 0.01452 0.00813 -0.0524 0.1361 1.0000
8.750 1.1626 0.01510 0.00862 -0.0503 0.1182 1.0000
9.000 1.1771 0.01568 0.00914 -0.0483 0.1037 1.0000
9.250 1.1917 0.01627 0.00969 -0.0463 0.0910 1.0000
9.500 1.2056 0.01691 0.01028 -0.0443 0.0787 1.0000
9.750 1.2188 0.01760 0.01092 -0.0423 0.0667 1.0000
10.000 1.2309 0.01837 0.01165 -0.0403 0.0548 1.0000
10.250 1.2411 0.01926 0.01248 -0.0380 0.0427 1.0000
10.500 1.2472 0.02045 0.01356 -0.0354 0.0276 1.0000
10.750 1.2520 0.02177 0.01483 -0.0327 0.0182 1.0000
11.000 1.2593 0.02298 0.01607 -0.0304 0.0156 1.0000
11.250 1.2693 0.02403 0.01719 -0.0286 0.0140 1.0000
11.500 1.2760 0.02534 0.01856 -0.0266 0.0129 1.0000
11.750 1.2793 0.02695 0.02026 -0.0245 0.0122 1.0000
12.000 1.2874 0.02826 0.02167 -0.0229 0.0118 1.0000
12.250 1.2938 0.02973 0.02324 -0.0214 0.0114 1.0000
12.500 1.2988 0.03138 0.02497 -0.0199 0.0109 1.0000
12.750 1.3027 0.03316 0.02685 -0.0185 0.0106 1.0000
13.000 1.3057 0.03510 0.02887 -0.0172 0.0103 1.0000
13.250 1.3076 0.03719 0.03106 -0.0161 0.0101 1.0000
13.500 1.3059 0.03971 0.03367 -0.0150 0.0098 1.0000
13.750 1.3020 0.04256 0.03662 -0.0141 0.0096 1.0000
14.000 1.2957 0.04578 0.03995 -0.0134 0.0094 1.0000
14.250 1.2909 0.04901 0.04329 -0.0130 0.0094 1.0000
14.500 1.2845 0.05258 0.04699 -0.0129 0.0092 1.0000
14.750 1.2845 0.05558 0.05010 -0.0130 0.0092 1.0000
15.000 1.2842 0.05874 0.05337 -0.0133 0.0091 1.0000
15.250 1.2814 0.06229 0.05704 -0.0138 0.0091 1.0000
15.500 1.2794 0.06593 0.06082 -0.0146 0.0088 1.0000
15.750 1.2771 0.06969 0.06469 -0.0155 0.0088 1.0000
16.000 1.2741 0.07365 0.06878 -0.0166 0.0087 1.0000
16.250 1.2702 0.07791 0.07317 -0.0180 0.0085 1.0000
16.500 1.2666 0.08221 0.07758 -0.0196 0.0085 1.0000
16.750 1.2616 0.08685 0.08235 -0.0214 0.0083 1.0000
17.000 1.2559 0.09169 0.08732 -0.0233 0.0083 1.0000
17.250 1.2501 0.09664 0.09240 -0.0254 0.0083 1.0000
17.500 1.2440 0.10179 0.09768 -0.0278 0.0082 1.0000
17.750 1.2359 0.10736 0.10339 -0.0304 0.0082 1.0000
18.000 1.2293 0.11282 0.10897 -0.0332 0.0081 1.0000
18.250 1.2204 0.11881 0.11511 -0.0363 0.0081 1.0000
18.500 1.2110 0.12503 0.12148 -0.0397 0.0081 1.0000
18.750 1.2026 0.13120 0.12778 -0.0432 0.0081 1.0000
19.000 1.1915 0.13804 0.13476 -0.0472 0.0081 1.0000
19.250 1.1803 0.14507 0.14195 -0.0515 0.0081 1.0000
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Polar data table (+)
Polar graphs
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