AH 93-W-145 (ah93w145-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-145 (ah93w145-il) Reynolds number: 200,000 Max Cl/Cd: 79.32 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w145-il-200000.txt Download as CSV file: xf-ah93w145-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2013 0.08699 0.08362 -0.0607 0.8542 0.0746
-9.750 -0.2003 0.08339 0.07988 -0.0616 0.8297 0.0768
-9.500 -0.2086 0.07870 0.07511 -0.0642 0.8139 0.0799
-9.250 -0.4268 0.05704 0.05349 -0.0864 0.9083 0.0485
-9.000 -0.4200 0.05078 0.04689 -0.0908 0.8673 0.0477
-8.750 -0.4229 0.04520 0.04085 -0.0925 0.8383 0.0471
-8.500 -0.4232 0.03983 0.03493 -0.0931 0.8187 0.0465
-8.250 -0.4177 0.03499 0.02946 -0.0930 0.8032 0.0462
-8.000 -0.4051 0.03130 0.02515 -0.0925 0.7895 0.0466
-7.750 -0.3872 0.02875 0.02202 -0.0920 0.7774 0.0479
-7.500 -0.3675 0.02638 0.01917 -0.0916 0.7673 0.0498
-7.250 -0.3439 0.02521 0.01789 -0.0915 0.7576 0.0519
-7.000 -0.3193 0.02404 0.01652 -0.0913 0.7491 0.0541
-6.750 -0.2942 0.02288 0.01503 -0.0909 0.7415 0.0567
-6.500 -0.2691 0.02159 0.01347 -0.0907 0.7343 0.0599
-6.250 -0.2434 0.02082 0.01267 -0.0906 0.7271 0.0635
-6.000 -0.2168 0.02014 0.01179 -0.0904 0.7212 0.0675
-5.750 -0.1908 0.01917 0.01072 -0.0903 0.7146 0.0722
-5.500 -0.1641 0.01866 0.01016 -0.0902 0.7093 0.0776
-5.250 -0.1371 0.01810 0.00944 -0.0901 0.7044 0.0834
-5.000 -0.1108 0.01750 0.00891 -0.0901 0.6989 0.0906
-4.750 -0.0840 0.01695 0.00827 -0.0900 0.6940 0.0985
-4.500 -0.0568 0.01664 0.00790 -0.0900 0.6898 0.1083
-4.250 -0.0302 0.01614 0.00748 -0.0900 0.6846 0.1197
-4.000 -0.0031 0.01574 0.00711 -0.0900 0.6802 0.1344
-3.750 0.0243 0.01541 0.00676 -0.0901 0.6766 0.1542
-3.500 0.0513 0.01502 0.00650 -0.0902 0.6729 0.1811
-3.250 0.0782 0.01461 0.00628 -0.0904 0.6685 0.2210
-3.000 0.1050 0.01410 0.00607 -0.0907 0.6644 0.2876
-2.750 0.1309 0.01344 0.00594 -0.0908 0.6609 0.4220
-2.500 0.1558 0.01301 0.00604 -0.0904 0.6579 0.5711
-2.250 0.1799 0.01286 0.00624 -0.0894 0.6541 0.6670
-2.000 0.2040 0.01290 0.00644 -0.0881 0.6505 0.7287
-1.750 0.2282 0.01303 0.00660 -0.0869 0.6472 0.7728
-1.500 0.2520 0.01321 0.00674 -0.0854 0.6443 0.8063
-1.250 0.2754 0.01343 0.00693 -0.0840 0.6412 0.8345
-1.000 0.2962 0.01361 0.00715 -0.0820 0.6377 0.8570
-0.750 0.3170 0.01378 0.00731 -0.0801 0.6344 0.8790
-0.500 0.3377 0.01391 0.00740 -0.0780 0.6316 0.8994
-0.250 0.3583 0.01399 0.00743 -0.0760 0.6290 0.9176
0.000 0.3816 0.01410 0.00745 -0.0745 0.6265 0.9357
0.250 0.4088 0.01415 0.00752 -0.0742 0.6228 0.9535
0.500 0.4502 0.01423 0.00758 -0.0767 0.6195 0.9719
0.750 0.5112 0.01434 0.00761 -0.0834 0.6163 0.9850
1.000 0.5598 0.01442 0.00760 -0.0880 0.6135 0.9928
1.250 0.6063 0.01456 0.00763 -0.0922 0.6110 0.9996
1.500 0.6270 0.01476 0.00789 -0.0915 0.6076 1.0000
1.750 0.6467 0.01499 0.00814 -0.0906 0.6045 1.0000
2.000 0.6669 0.01520 0.00835 -0.0897 0.6015 1.0000
2.250 0.6881 0.01539 0.00851 -0.0888 0.5988 1.0000
2.500 0.7104 0.01560 0.00867 -0.0881 0.5964 1.0000
2.750 0.7329 0.01592 0.00897 -0.0875 0.5940 1.0000
3.000 0.7547 0.01628 0.00941 -0.0869 0.5904 1.0000
3.250 0.7799 0.01657 0.00974 -0.0869 0.5870 1.0000
3.500 0.8071 0.01683 0.01000 -0.0871 0.5840 1.0000
3.750 0.8356 0.01707 0.01022 -0.0875 0.5815 1.0000
4.000 0.8648 0.01735 0.01046 -0.0880 0.5793 1.0000
4.250 0.8892 0.01782 0.01106 -0.0879 0.5754 1.0000
4.500 0.9154 0.01820 0.01151 -0.0881 0.5716 1.0000
4.750 0.9433 0.01847 0.01180 -0.0884 0.5683 1.0000
5.000 0.9725 0.01867 0.01202 -0.0888 0.5656 1.0000
5.250 1.0026 0.01891 0.01222 -0.0893 0.5631 1.0000
5.500 1.0245 0.01944 0.01294 -0.0889 0.5577 1.0000
5.750 1.0517 0.01966 0.01322 -0.0890 0.5535 1.0000
6.000 1.0818 0.01966 0.01321 -0.0894 0.5499 1.0000
6.250 1.1094 0.01980 0.01339 -0.0895 0.5452 1.0000
6.500 1.1341 0.01994 0.01365 -0.0892 0.5387 1.0000
6.750 1.1652 0.01971 0.01340 -0.0895 0.5341 1.0000
7.000 1.1913 0.01982 0.01359 -0.0893 0.5284 1.0000
7.250 1.2175 0.01977 0.01363 -0.0891 0.5217 1.0000
7.500 1.2505 0.01935 0.01313 -0.0896 0.5166 1.0000
7.750 1.2716 0.01945 0.01342 -0.0887 0.5079 1.0000
8.000 1.3031 0.01899 0.01291 -0.0889 0.5017 1.0000
8.250 1.3244 0.01904 0.01316 -0.0880 0.4926 1.0000
8.500 1.3532 0.01866 0.01277 -0.0878 0.4848 1.0000
8.750 1.3754 0.01846 0.01270 -0.0868 0.4734 1.0000
9.000 1.3970 0.01828 0.01265 -0.0857 0.4604 1.0000
9.250 1.4181 0.01816 0.01262 -0.0845 0.4454 1.0000
9.500 1.4381 0.01813 0.01262 -0.0831 0.4274 1.0000
9.750 1.4545 0.01834 0.01290 -0.0813 0.4032 1.0000
10.000 1.4666 0.01877 0.01326 -0.0789 0.3700 1.0000
10.250 1.4690 0.01972 0.01400 -0.0752 0.3263 1.0000
10.500 1.4598 0.02122 0.01526 -0.0702 0.2858 1.0000
10.750 1.4467 0.02332 0.01715 -0.0656 0.2510 1.0000
11.000 1.4331 0.02595 0.01963 -0.0622 0.2210 1.0000
11.250 1.4205 0.02907 0.02265 -0.0600 0.1943 1.0000
11.500 1.4086 0.03252 0.02600 -0.0586 0.1706 1.0000
11.750 1.3963 0.03621 0.02960 -0.0574 0.1502 1.0000
12.000 1.3856 0.03984 0.03315 -0.0565 0.1310 1.0000
12.250 1.3748 0.04353 0.03677 -0.0556 0.1141 1.0000
12.500 1.3641 0.04723 0.04041 -0.0547 0.0997 1.0000
12.750 1.3539 0.05091 0.04404 -0.0539 0.0872 1.0000
13.000 1.3448 0.05453 0.04763 -0.0532 0.0768 1.0000
13.250 1.3362 0.05822 0.05129 -0.0526 0.0684 1.0000
13.500 1.3273 0.06202 0.05506 -0.0521 0.0618 1.0000
13.750 1.3247 0.06520 0.05831 -0.0517 0.0556 1.0000
14.000 1.3166 0.06902 0.06206 -0.0513 0.0513 1.0000
14.250 1.3177 0.07188 0.06502 -0.0510 0.0471 1.0000
14.500 1.3157 0.07508 0.06824 -0.0508 0.0440 1.0000
14.750 1.3138 0.07810 0.07125 -0.0502 0.0415 1.0000
15.000 1.3168 0.08074 0.07400 -0.0499 0.0391 1.0000
15.250 1.3190 0.08347 0.07676 -0.0497 0.0371 1.0000
15.500 1.3212 0.08588 0.07912 -0.0490 0.0352 1.0000
15.750 1.3263 0.08807 0.08141 -0.0484 0.0336 1.0000
16.000 1.3304 0.09064 0.08409 -0.0483 0.0321 1.0000
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Polar data table (+)
Polar graphs
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