AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 50,000 Max Cl/Cd: 18.68 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93w145-il-50000-n5.txt Download as CSV file: xf-ah93w145-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3515 0.10113 0.09437 -0.0479 1.0000 0.0668
-9.750 -0.3555 0.09666 0.09001 -0.0500 1.0000 0.0670
-9.500 -0.3616 0.09208 0.08555 -0.0522 1.0000 0.0671
-9.250 -0.3703 0.08746 0.08107 -0.0544 1.0000 0.0670
-9.000 -0.3841 0.08297 0.07676 -0.0561 1.0000 0.0667
-8.750 -0.4023 0.07795 0.07192 -0.0595 0.9899 0.0661
-8.500 -0.4057 0.06923 0.06306 -0.0701 0.9510 0.0657
-8.250 -0.4064 0.06155 0.05504 -0.0778 0.9246 0.0657
-8.000 -0.4004 0.05505 0.04805 -0.0832 0.9047 0.0666
-7.750 -0.3909 0.04922 0.04147 -0.0870 0.8880 0.0688
-7.500 -0.3709 0.04563 0.03745 -0.0891 0.8737 0.0715
-7.250 -0.3467 0.04315 0.03468 -0.0904 0.8608 0.0741
-7.000 -0.3235 0.04038 0.03141 -0.0915 0.8491 0.0776
-6.750 -0.3016 0.03756 0.02778 -0.0920 0.8374 0.0824
-6.500 -0.2773 0.03600 0.02614 -0.0922 0.8263 0.0861
-6.250 -0.2514 0.03442 0.02422 -0.0925 0.8171 0.0916
-6.000 -0.2267 0.03288 0.02228 -0.0924 0.8072 0.0977
-5.750 -0.2012 0.03178 0.02105 -0.0923 0.7986 0.1038
-5.500 -0.1751 0.03065 0.01960 -0.0922 0.7903 0.1121
-5.250 -0.1495 0.02977 0.01861 -0.0919 0.7826 0.1204
-5.000 -0.1238 0.02896 0.01769 -0.0917 0.7751 0.1308
-4.750 -0.0974 0.02820 0.01675 -0.0914 0.7685 0.1426
-4.500 -0.0727 0.02761 0.01609 -0.0910 0.7612 0.1573
-4.250 -0.0462 0.02695 0.01539 -0.0908 0.7557 0.1746
-4.000 -0.0226 0.02645 0.01492 -0.0904 0.7488 0.1962
-3.750 0.0020 0.02588 0.01440 -0.0902 0.7430 0.2248
-3.500 0.0269 0.02526 0.01390 -0.0899 0.7382 0.2656
-3.250 0.0481 0.02473 0.01372 -0.0895 0.7317 0.3234
-3.000 0.0694 0.02408 0.01359 -0.0886 0.7266 0.4259
-2.750 0.0891 0.02366 0.01373 -0.0862 0.7226 0.5613
-2.500 0.1046 0.02384 0.01424 -0.0829 0.7167 0.6642
-2.250 0.1230 0.02411 0.01456 -0.0798 0.7118 0.7411
-2.000 0.1443 0.02436 0.01469 -0.0771 0.7079 0.8006
-1.750 0.1646 0.02472 0.01496 -0.0749 0.7029 0.8476
-1.500 0.1902 0.02501 0.01513 -0.0738 0.6980 0.8894
-1.250 0.2285 0.02514 0.01504 -0.0751 0.6941 0.9295
-1.000 0.2983 0.02506 0.01465 -0.0825 0.6910 0.9683
-0.750 0.3708 0.02516 0.01452 -0.0921 0.6858 0.9982
-0.500 0.3878 0.02551 0.01475 -0.0914 0.6810 1.0000
-0.250 0.4044 0.02579 0.01489 -0.0902 0.6773 1.0000
0.000 0.4215 0.02611 0.01507 -0.0890 0.6738 1.0000
0.250 0.4295 0.02682 0.01575 -0.0868 0.6682 1.0000
0.500 0.4440 0.02730 0.01614 -0.0853 0.6638 1.0000
0.750 0.4637 0.02767 0.01639 -0.0843 0.6604 1.0000
1.000 0.4801 0.02830 0.01693 -0.0832 0.6564 1.0000
1.250 0.4929 0.02919 0.01779 -0.0820 0.6510 1.0000
1.500 0.5141 0.02975 0.01827 -0.0815 0.6470 1.0000
1.750 0.5394 0.03017 0.01860 -0.0814 0.6440 1.0000
2.000 0.5547 0.03120 0.01960 -0.0806 0.6391 1.0000
2.250 0.5704 0.03224 0.02064 -0.0799 0.6339 1.0000
2.500 0.5942 0.03285 0.02120 -0.0798 0.6302 1.0000
2.750 0.6217 0.03329 0.02158 -0.0800 0.6275 1.0000
3.000 0.6286 0.03501 0.02334 -0.0788 0.6209 1.0000
3.250 0.6471 0.03602 0.02437 -0.0784 0.6161 1.0000
3.500 0.6732 0.03659 0.02492 -0.0785 0.6129 1.0000
3.750 0.6929 0.03761 0.02594 -0.0782 0.6088 1.0000
4.000 0.6967 0.03966 0.02805 -0.0769 0.6013 1.0000
4.250 0.7212 0.04036 0.02878 -0.0769 0.5977 1.0000
4.500 0.7510 0.04072 0.02916 -0.0771 0.5952 1.0000
5.000 0.7660 0.04448 0.03304 -0.0752 0.5816 1.0000
5.250 0.7859 0.04555 0.03417 -0.0749 0.5773 1.0000
5.500 0.7800 0.04833 0.03702 -0.0732 0.5678 1.0000
5.750 0.8084 0.04876 0.03751 -0.0733 0.5647 1.0000
6.250 0.8226 0.05277 0.04165 -0.0717 0.5499 1.0000
6.500 0.8553 0.05276 0.04175 -0.0716 0.5473 1.0000
7.000 0.8514 0.05819 0.04733 -0.0696 0.5280 1.0000
7.250 0.8625 0.05983 0.04906 -0.0690 0.5202 1.0000
7.500 0.8952 0.05971 0.04908 -0.0687 0.5169 1.0000
7.750 0.8868 0.06288 0.05233 -0.0676 0.5049 1.0000
8.000 0.9087 0.06355 0.05311 -0.0671 0.4991 1.0000
8.250 0.9143 0.06550 0.05517 -0.0662 0.4891 1.0000
8.750 0.9448 0.06766 0.05760 -0.0647 0.4729 1.0000
9.000 0.9452 0.07002 0.06007 -0.0638 0.4612 1.0000
9.250 0.9793 0.06918 0.05940 -0.0630 0.4565 1.0000
9.500 0.9778 0.07166 0.06200 -0.0621 0.4437 1.0000
9.750 0.9811 0.07370 0.06416 -0.0613 0.4318 1.0000
10.000 1.0169 0.07224 0.06292 -0.0601 0.4266 1.0000
10.250 1.0181 0.07438 0.06519 -0.0593 0.4133 1.0000
10.500 1.0221 0.07626 0.06720 -0.0584 0.4003 1.0000
10.750 1.0292 0.07775 0.06883 -0.0576 0.3876 1.0000
11.250 1.0760 0.07623 0.06773 -0.0548 0.3678 1.0000
11.500 1.0845 0.07726 0.06892 -0.0538 0.3538 1.0000
11.750 1.0954 0.07790 0.06973 -0.0527 0.3397 1.0000
12.000 1.1096 0.07804 0.07003 -0.0515 0.3252 1.0000
12.250 1.1279 0.07752 0.06969 -0.0501 0.3098 1.0000
12.500 1.1397 0.07802 0.07031 -0.0489 0.2916 1.0000
12.750 1.1516 0.07855 0.07091 -0.0477 0.2712 1.0000
13.000 1.1717 0.07770 0.07000 -0.0460 0.2480 1.0000
13.250 1.1777 0.07917 0.07140 -0.0450 0.2243 1.0000
13.500 1.1800 0.08128 0.07337 -0.0442 0.2023 1.0000
13.750 1.1783 0.08418 0.07614 -0.0439 0.1823 1.0000
14.000 1.1762 0.08721 0.07902 -0.0436 0.1647 1.0000
14.250 1.1730 0.09052 0.08220 -0.0436 0.1492 1.0000
14.500 1.1698 0.09402 0.08562 -0.0438 0.1353 1.0000
14.750 1.1670 0.09759 0.08917 -0.0441 0.1229 1.0000
15.000 1.1649 0.10117 0.09277 -0.0444 0.1118 1.0000
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Polar data table (+)
Polar graphs
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