AH 93-W-174 (ah93w174-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-174 (ah93w174-il) Reynolds number: 200,000 Max Cl/Cd: 65.48 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w174-il-200000.txt Download as CSV file: xf-ah93w174-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-174
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3678 0.09103 0.08740 -0.0750 0.8911 0.0613
-12.250 -0.3497 0.08359 0.07972 -0.0846 0.8528 0.0623
-12.000 -0.6272 0.04271 0.03763 -0.1101 0.8520 0.0543
-11.750 -0.6184 0.04083 0.03549 -0.1107 0.8227 0.0552
-11.500 -0.6140 0.03963 0.03411 -0.1092 0.8027 0.0561
-11.250 -0.6153 0.03815 0.03238 -0.1070 0.7879 0.0569
-11.000 -0.6136 0.03661 0.03059 -0.1051 0.7749 0.0581
-10.750 -0.6120 0.03485 0.02850 -0.1031 0.7645 0.0593
-10.500 -0.6079 0.03323 0.02646 -0.1011 0.7553 0.0606
-10.250 -0.5991 0.03142 0.02430 -0.0996 0.7472 0.0617
-10.000 -0.5796 0.02995 0.02280 -0.0991 0.7396 0.0633
-9.750 -0.5604 0.02914 0.02189 -0.0984 0.7330 0.0651
-9.500 -0.5418 0.02827 0.02087 -0.0975 0.7258 0.0673
-9.250 -0.5237 0.02736 0.01966 -0.0965 0.7199 0.0696
-9.000 -0.5040 0.02598 0.01809 -0.0958 0.7140 0.0718
-8.750 -0.4812 0.02515 0.01728 -0.0954 0.7079 0.0742
-8.500 -0.4588 0.02456 0.01657 -0.0948 0.7030 0.0772
-8.250 -0.4364 0.02399 0.01577 -0.0942 0.6985 0.0803
-8.000 -0.4134 0.02288 0.01465 -0.0938 0.6934 0.0835
-7.750 -0.3896 0.02235 0.01411 -0.0934 0.6886 0.0872
-7.500 -0.3655 0.02190 0.01347 -0.0929 0.6844 0.0914
-7.250 -0.3418 0.02111 0.01267 -0.0925 0.6802 0.0959
-7.000 -0.3177 0.02067 0.01225 -0.0921 0.6755 0.1007
-6.750 -0.2929 0.02027 0.01169 -0.0917 0.6714 0.1061
-6.500 -0.2686 0.01967 0.01116 -0.0913 0.6679 0.1123
-6.250 -0.2429 0.01946 0.01077 -0.0910 0.6648 0.1191
-6.000 -0.2193 0.01888 0.01034 -0.0906 0.6609 0.1265
-5.750 -0.1942 0.01856 0.00996 -0.0903 0.6568 0.1351
-5.500 -0.1695 0.01816 0.00961 -0.0900 0.6531 0.1449
-5.250 -0.1443 0.01779 0.00924 -0.0897 0.6499 0.1559
-5.000 -0.1187 0.01754 0.00896 -0.0895 0.6471 0.1691
-4.750 -0.0939 0.01725 0.00876 -0.0892 0.6437 0.1841
-4.500 -0.0690 0.01696 0.00856 -0.0889 0.6402 0.2018
-4.250 -0.0437 0.01666 0.00836 -0.0887 0.6369 0.2230
-4.000 -0.0177 0.01640 0.00814 -0.0885 0.6339 0.2495
-3.750 0.0081 0.01612 0.00796 -0.0884 0.6312 0.2811
-3.500 0.0332 0.01588 0.00789 -0.0882 0.6282 0.3203
-3.250 0.0577 0.01561 0.00788 -0.0880 0.6250 0.3700
-3.000 0.0825 0.01537 0.00790 -0.0877 0.6219 0.4291
-2.750 0.1080 0.01521 0.00796 -0.0873 0.6190 0.4909
-2.500 0.1342 0.01515 0.00804 -0.0869 0.6164 0.5451
-2.250 0.1609 0.01520 0.00816 -0.0865 0.6139 0.5885
-2.000 0.1868 0.01537 0.00840 -0.0860 0.6111 0.6237
-1.750 0.2122 0.01554 0.00866 -0.0854 0.6079 0.6535
-1.500 0.2377 0.01574 0.00893 -0.0848 0.6050 0.6781
-1.250 0.2638 0.01595 0.00914 -0.0842 0.6022 0.7008
-1.000 0.2903 0.01613 0.00930 -0.0836 0.5997 0.7207
-0.750 0.3168 0.01633 0.00946 -0.0831 0.5973 0.7382
-0.500 0.3431 0.01663 0.00972 -0.0824 0.5951 0.7539
-0.250 0.3658 0.01690 0.01010 -0.0813 0.5920 0.7682
0.000 0.3894 0.01718 0.01042 -0.0804 0.5890 0.7823
0.250 0.4139 0.01742 0.01066 -0.0796 0.5862 0.7964
0.500 0.4384 0.01762 0.01085 -0.0787 0.5836 0.8098
0.750 0.4625 0.01777 0.01099 -0.0775 0.5813 0.8215
1.000 0.4874 0.01795 0.01112 -0.0766 0.5792 0.8339
1.250 0.5096 0.01826 0.01146 -0.0755 0.5768 0.8472
1.500 0.5275 0.01860 0.01190 -0.0735 0.5736 0.8600
1.750 0.5463 0.01883 0.01219 -0.0716 0.5706 0.8721
2.000 0.5675 0.01896 0.01233 -0.0702 0.5679 0.8844
2.250 0.5904 0.01903 0.01238 -0.0691 0.5654 0.8968
2.500 0.6132 0.01907 0.01240 -0.0678 0.5634 0.9081
2.750 0.6372 0.01918 0.01248 -0.0669 0.5617 0.9191
3.000 0.6544 0.01954 0.01294 -0.0652 0.5587 0.9320
3.250 0.6741 0.01987 0.01337 -0.0641 0.5548 0.9453
3.500 0.7034 0.02004 0.01357 -0.0647 0.5517 0.9570
3.750 0.7412 0.02018 0.01371 -0.0669 0.5493 0.9661
4.000 0.7835 0.02033 0.01382 -0.0700 0.5472 0.9735
4.250 0.8267 0.02045 0.01390 -0.0732 0.5453 0.9807
4.500 0.8667 0.02103 0.01457 -0.0765 0.5417 0.9882
4.750 0.9035 0.02169 0.01535 -0.0796 0.5375 0.9990
5.000 0.9128 0.02205 0.01574 -0.0771 0.5346 1.0000
5.250 0.9326 0.02221 0.01589 -0.0762 0.5321 1.0000
5.500 0.9607 0.02231 0.01596 -0.0766 0.5301 1.0000
5.750 0.9920 0.02245 0.01606 -0.0774 0.5284 1.0000
6.000 1.0037 0.02360 0.01736 -0.0761 0.5236 1.0000
6.250 1.0236 0.02427 0.01813 -0.0757 0.5193 1.0000
6.500 1.0524 0.02447 0.01834 -0.0762 0.5166 1.0000
6.750 1.0835 0.02451 0.01837 -0.0769 0.5144 1.0000
7.000 1.1177 0.02443 0.01826 -0.0780 0.5125 1.0000
7.250 1.1327 0.02539 0.01934 -0.0768 0.5081 1.0000
7.500 1.1461 0.02627 0.02034 -0.0755 0.5028 1.0000
7.750 1.1775 0.02610 0.02019 -0.0760 0.4998 1.0000
8.000 1.2134 0.02571 0.01977 -0.0770 0.4975 1.0000
8.250 1.2528 0.02524 0.01925 -0.0785 0.4955 1.0000
8.500 1.2498 0.02676 0.02101 -0.0751 0.4884 1.0000
8.750 1.2788 0.02653 0.02081 -0.0752 0.4844 1.0000
9.000 1.3196 0.02569 0.01993 -0.0766 0.4815 1.0000
9.250 1.3614 0.02493 0.01912 -0.0783 0.4785 1.0000
9.500 1.3581 0.02603 0.02045 -0.0744 0.4709 1.0000
9.750 1.3984 0.02492 0.01930 -0.0756 0.4662 1.0000
10.000 1.4287 0.02434 0.01873 -0.0757 0.4606 1.0000
10.250 1.4413 0.02439 0.01890 -0.0735 0.4532 1.0000
10.500 1.4864 0.02314 0.01753 -0.0753 0.4474 1.0000
10.750 1.4812 0.02393 0.01854 -0.0708 0.4396 1.0000
11.000 1.5135 0.02319 0.01775 -0.0710 0.4327 1.0000
11.250 1.5061 0.02386 0.01859 -0.0660 0.4249 1.0000
11.500 1.5295 0.02336 0.01803 -0.0650 0.4162 1.0000
11.750 1.5135 0.02458 0.01942 -0.0596 0.4075 1.0000
12.000 1.5188 0.02507 0.01993 -0.0570 0.3978 1.0000
12.250 1.5176 0.02607 0.02097 -0.0543 0.3871 1.0000
12.500 1.5061 0.02803 0.02303 -0.0514 0.3756 1.0000
12.750 1.4995 0.02998 0.02502 -0.0493 0.3631 1.0000
13.000 1.4923 0.03220 0.02725 -0.0474 0.3492 1.0000
13.250 1.4826 0.03482 0.02986 -0.0458 0.3338 1.0000
13.500 1.4722 0.03766 0.03267 -0.0444 0.3170 1.0000
13.750 1.4607 0.04070 0.03566 -0.0431 0.2990 1.0000
14.000 1.4478 0.04396 0.03882 -0.0419 0.2801 1.0000
14.250 1.4333 0.04760 0.04238 -0.0410 0.2607 1.0000
14.500 1.4192 0.05141 0.04611 -0.0404 0.2415 1.0000
14.750 1.4048 0.05541 0.05000 -0.0399 0.2229 1.0000
15.000 1.3905 0.05959 0.05407 -0.0397 0.2052 1.0000
15.250 1.3778 0.06379 0.05820 -0.0397 0.1880 1.0000
15.500 1.3660 0.06805 0.06240 -0.0399 0.1712 1.0000
15.750 1.3547 0.07240 0.06667 -0.0403 0.1553 1.0000
16.000 1.3441 0.07678 0.07098 -0.0408 0.1403 1.0000
16.250 1.3338 0.08125 0.07539 -0.0414 0.1262 1.0000
16.500 1.3246 0.08568 0.07976 -0.0422 0.1137 1.0000
16.750 1.3165 0.09007 0.08410 -0.0431 0.1023 1.0000
17.000 1.3087 0.09448 0.08845 -0.0440 0.0924 1.0000
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Polar data table (+)
Polar graphs
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