AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 500,000 Max Cl/Cd: 116.25 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w145-il-500000-n5.txt Download as CSV file: xf-ah93w145-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-145
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8085 0.06891 0.06584 -0.0579 1.0000 0.0120
-14.250 -0.8559 0.05469 0.05134 -0.0684 1.0000 0.0118
-14.000 -0.8813 0.04521 0.04162 -0.0770 1.0000 0.0118
-13.750 -0.8949 0.03966 0.03588 -0.0815 1.0000 0.0118
-13.500 -0.9064 0.03580 0.03187 -0.0833 1.0000 0.0119
-13.250 -0.9162 0.03316 0.02910 -0.0827 1.0000 0.0120
-13.000 -0.9264 0.03134 0.02719 -0.0800 1.0000 0.0121
-12.750 -0.9230 0.02973 0.02547 -0.0785 0.9989 0.0123
-12.500 -0.9001 0.02806 0.02367 -0.0804 0.9861 0.0125
-12.250 -0.8625 0.02640 0.02185 -0.0849 0.9416 0.0128
-12.000 -0.8230 0.02505 0.02008 -0.0891 0.8500 0.0132
-11.750 -0.8060 0.02423 0.01896 -0.0883 0.8092 0.0136
-11.500 -0.7873 0.02341 0.01791 -0.0877 0.7822 0.0139
-11.250 -0.7675 0.02261 0.01689 -0.0872 0.7602 0.0143
-11.000 -0.7465 0.02185 0.01592 -0.0868 0.7415 0.0147
-10.750 -0.7255 0.02105 0.01493 -0.0864 0.7251 0.0151
-10.500 -0.7040 0.02024 0.01399 -0.0861 0.7104 0.0155
-10.250 -0.6809 0.01961 0.01323 -0.0858 0.6974 0.0159
-10.000 -0.6571 0.01904 0.01253 -0.0856 0.6863 0.0164
-9.750 -0.6329 0.01848 0.01184 -0.0854 0.6763 0.0169
-9.500 -0.6082 0.01792 0.01116 -0.0853 0.6677 0.0175
-9.250 -0.5833 0.01742 0.01052 -0.0851 0.6595 0.0181
-9.000 -0.5581 0.01689 0.00987 -0.0850 0.6520 0.0187
-8.750 -0.5328 0.01638 0.00930 -0.0849 0.6446 0.0196
-8.500 -0.5067 0.01599 0.00883 -0.0849 0.6382 0.0205
-8.250 -0.4804 0.01560 0.00835 -0.0849 0.6321 0.0214
-7.750 -0.4276 0.01479 0.00736 -0.0848 0.6222 0.0234
-7.500 -0.4008 0.01443 0.00695 -0.0849 0.6173 0.0246
-7.250 -0.3737 0.01414 0.00659 -0.0849 0.6127 0.0261
-7.000 -0.3464 0.01387 0.00623 -0.0849 0.6085 0.0275
-6.750 -0.3192 0.01351 0.00586 -0.0850 0.6041 0.0295
-6.500 -0.2917 0.01325 0.00555 -0.0851 0.6000 0.0314
-6.250 -0.2641 0.01303 0.00525 -0.0852 0.5964 0.0333
-6.000 -0.2365 0.01275 0.00495 -0.0853 0.5933 0.0358
-5.750 -0.2084 0.01253 0.00470 -0.0854 0.5900 0.0388
-5.500 -0.1804 0.01231 0.00445 -0.0856 0.5866 0.0416
-5.250 -0.1525 0.01210 0.00421 -0.0857 0.5832 0.0453
-5.000 -0.1244 0.01195 0.00400 -0.0859 0.5800 0.0487
-4.750 -0.0962 0.01173 0.00379 -0.0860 0.5771 0.0535
-4.500 -0.0677 0.01157 0.00361 -0.0862 0.5742 0.0582
-4.250 -0.0393 0.01138 0.00343 -0.0865 0.5714 0.0646
-4.000 -0.0109 0.01124 0.00327 -0.0867 0.5687 0.0709
-3.750 0.0175 0.01109 0.00312 -0.0869 0.5660 0.0798
-3.500 0.0458 0.01095 0.00298 -0.0871 0.5634 0.0898
-3.250 0.0745 0.01080 0.00287 -0.0873 0.5609 0.1021
-3.000 0.1033 0.01065 0.00275 -0.0876 0.5581 0.1165
-2.750 0.1320 0.01051 0.00266 -0.0879 0.5555 0.1344
-2.500 0.1606 0.01038 0.00257 -0.0882 0.5531 0.1545
-2.250 0.1893 0.01024 0.00249 -0.0884 0.5508 0.1786
-2.000 0.2179 0.01011 0.00242 -0.0887 0.5486 0.2078
-1.750 0.2466 0.00994 0.00236 -0.0891 0.5463 0.2467
-1.500 0.2754 0.00969 0.00230 -0.0895 0.5439 0.3030
-1.000 0.3328 0.00912 0.00224 -0.0904 0.5391 0.4668
-0.750 0.3615 0.00891 0.00225 -0.0908 0.5369 0.5405
-0.500 0.3901 0.00876 0.00227 -0.0911 0.5348 0.6008
-0.250 0.4185 0.00868 0.00231 -0.0912 0.5326 0.6523
0.000 0.4468 0.00861 0.00237 -0.0913 0.5305 0.6964
0.250 0.4752 0.00858 0.00243 -0.0914 0.5282 0.7290
0.500 0.5035 0.00858 0.00250 -0.0914 0.5259 0.7554
0.750 0.5315 0.00859 0.00257 -0.0914 0.5237 0.7792
1.000 0.5595 0.00863 0.00264 -0.0913 0.5216 0.8025
1.250 0.5860 0.00867 0.00274 -0.0909 0.5195 0.8300
1.500 0.6130 0.00875 0.00283 -0.0906 0.5173 0.8493
1.750 0.6404 0.00881 0.00291 -0.0905 0.5152 0.8593
2.000 0.6686 0.00886 0.00299 -0.0906 0.5132 0.8687
2.250 0.6961 0.00891 0.00307 -0.0905 0.5110 0.8769
2.500 0.7240 0.00897 0.00315 -0.0905 0.5086 0.8848
2.750 0.7511 0.00903 0.00322 -0.0903 0.5062 0.8923
3.000 0.7789 0.00911 0.00330 -0.0903 0.5040 0.8998
3.250 0.8054 0.00919 0.00338 -0.0900 0.5019 0.9068
3.500 0.8331 0.00927 0.00348 -0.0900 0.4997 0.9141
3.750 0.8593 0.00931 0.00358 -0.0897 0.4972 0.9211
4.000 0.8865 0.00937 0.00368 -0.0896 0.4946 0.9287
4.250 0.9120 0.00942 0.00376 -0.0891 0.4919 0.9362
4.500 0.9383 0.00948 0.00385 -0.0888 0.4893 0.9444
4.750 0.9638 0.00955 0.00393 -0.0883 0.4866 0.9533
5.000 0.9907 0.00960 0.00403 -0.0882 0.4833 0.9632
5.250 1.0197 0.00963 0.00412 -0.0885 0.4782 0.9751
5.500 1.0505 0.00969 0.00417 -0.0893 0.4720 1.0000
5.750 1.0793 0.00978 0.00430 -0.0898 0.4655 1.0000
6.000 1.1077 0.00989 0.00443 -0.0901 0.4593 1.0000
6.250 1.1358 0.01002 0.00459 -0.0904 0.4530 1.0000
6.500 1.1637 0.01015 0.00474 -0.0906 0.4447 1.0000
6.750 1.1911 0.01030 0.00490 -0.0908 0.4352 1.0000
7.000 1.2177 0.01049 0.00508 -0.0908 0.4237 1.0000
7.250 1.2439 0.01070 0.00530 -0.0907 0.4110 1.0000
7.500 1.2694 0.01096 0.00554 -0.0906 0.3947 1.0000
7.750 1.2917 0.01141 0.00588 -0.0899 0.3648 1.0000
8.000 1.3078 0.01231 0.00651 -0.0884 0.3136 1.0000
8.250 1.3196 0.01350 0.00739 -0.0863 0.2598 1.0000
8.500 1.3310 0.01466 0.00830 -0.0842 0.2151 1.0000
8.750 1.3414 0.01580 0.00923 -0.0820 0.1782 1.0000
9.250 1.3591 0.01782 0.01101 -0.0770 0.1269 1.0000
9.750 1.3730 0.02000 0.01306 -0.0719 0.0939 1.0000
10.000 1.3795 0.02126 0.01429 -0.0698 0.0812 1.0000
10.250 1.3850 0.02274 0.01574 -0.0681 0.0700 1.0000
10.500 1.3901 0.02444 0.01743 -0.0667 0.0606 1.0000
10.750 1.3961 0.02626 0.01927 -0.0657 0.0526 1.0000
11.000 1.4020 0.02819 0.02122 -0.0650 0.0463 1.0000
11.250 1.4069 0.03031 0.02335 -0.0643 0.0407 1.0000
11.500 1.4112 0.03250 0.02557 -0.0637 0.0358 1.0000
11.750 1.4158 0.03469 0.02780 -0.0631 0.0319 1.0000
12.250 1.4220 0.03936 0.03255 -0.0619 0.0255 1.0000
12.500 1.4235 0.04186 0.03508 -0.0613 0.0230 1.0000
12.750 1.4265 0.04419 0.03748 -0.0607 0.0211 1.0000
13.000 1.4280 0.04668 0.04001 -0.0601 0.0194 1.0000
13.250 1.4291 0.04921 0.04259 -0.0595 0.0181 1.0000
13.500 1.4315 0.05165 0.04510 -0.0590 0.0170 1.0000
13.750 1.4332 0.05419 0.04770 -0.0585 0.0160 1.0000
14.000 1.4340 0.05690 0.05046 -0.0582 0.0151 1.0000
14.250 1.4355 0.05960 0.05323 -0.0579 0.0144 1.0000
14.500 1.4381 0.06219 0.05590 -0.0576 0.0138 1.0000
14.750 1.4396 0.06495 0.05873 -0.0575 0.0132 1.0000
15.000 1.4412 0.06773 0.06158 -0.0573 0.0126 1.0000
15.250 1.4415 0.07071 0.06462 -0.0573 0.0121 1.0000
15.500 1.4404 0.07389 0.06787 -0.0573 0.0116 1.0000
15.750 1.4416 0.07682 0.07087 -0.0573 0.0113 1.0000
16.000 1.4425 0.07982 0.07396 -0.0574 0.0109 1.0000
16.250 1.4433 0.08286 0.07708 -0.0576 0.0105 1.0000
16.500 1.4430 0.08609 0.08039 -0.0579 0.0102 1.0000
16.750 1.4428 0.08933 0.08371 -0.0582 0.0099 1.0000
17.000 1.4410 0.09281 0.08727 -0.0586 0.0097 1.0000
17.250 1.4389 0.09636 0.09090 -0.0591 0.0094 1.0000
17.500 1.4353 0.10019 0.09481 -0.0597 0.0092 1.0000
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Polar data table (+)
Polar graphs
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