WORTMANN FX 75-141 (fx75141-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 75-141 (fx75141-il) Reynolds number: 100,000 Max Cl/Cd: 54.34 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx75141-il-100000.txt Download as CSV file: xf-fx75141-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 75-141
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4368 0.10083 0.09657 -0.0375 0.9932 0.1506
-8.250 -0.4229 0.09782 0.09353 -0.0385 0.9903 0.1559
-8.000 -0.4978 0.09318 0.08906 -0.0490 0.9819 0.1626
-7.750 -0.4393 0.08997 0.08577 -0.0442 0.9820 0.1667
-7.500 -0.4353 0.08705 0.08285 -0.0460 0.9784 0.1748
-7.250 -0.5598 0.05639 0.05095 -0.0710 0.9679 0.0858
-7.000 -0.5486 0.05160 0.04591 -0.0721 0.9645 0.0826
-6.750 -0.5367 0.04619 0.03989 -0.0736 0.9607 0.0795
-6.500 -0.5127 0.04300 0.03623 -0.0754 0.9572 0.0814
-6.250 -0.4807 0.03958 0.03222 -0.0781 0.9542 0.0826
-6.000 -0.4591 0.03718 0.02935 -0.0781 0.9503 0.0837
-5.750 -0.4329 0.03556 0.02717 -0.0786 0.9462 0.0870
-5.500 -0.4019 0.03353 0.02502 -0.0802 0.9426 0.0917
-5.250 -0.3634 0.03230 0.02357 -0.0825 0.9394 0.0975
-5.000 -0.3443 0.03135 0.02238 -0.0814 0.9345 0.1028
-4.750 -0.3171 0.03035 0.02145 -0.0818 0.9299 0.1099
-4.500 -0.2820 0.02944 0.02048 -0.0834 0.9260 0.1209
-4.250 -0.2511 0.02879 0.01982 -0.0842 0.9220 0.1337
-4.000 -0.2322 0.02828 0.01938 -0.0832 0.9162 0.1483
-3.750 -0.2007 0.02756 0.01889 -0.0843 0.9116 0.1746
-3.500 -0.1614 0.02655 0.01837 -0.0871 0.9081 0.2416
-3.250 -0.1510 0.02531 0.01834 -0.0853 0.9018 0.4193
-3.000 -0.1301 0.02566 0.01928 -0.0831 0.8960 0.5743
-2.750 -0.0947 0.02672 0.02031 -0.0831 0.8917 0.6356
-2.500 -0.0905 0.02746 0.02103 -0.0786 0.8834 0.6599
-2.250 -0.0630 0.02837 0.02186 -0.0773 0.8779 0.6894
-2.000 -0.0475 0.02912 0.02254 -0.0745 0.8710 0.7120
-1.750 -0.0297 0.02970 0.02306 -0.0721 0.8641 0.7333
-1.500 0.0013 0.03024 0.02354 -0.0712 0.8597 0.7541
-1.250 0.0016 0.03065 0.02394 -0.0666 0.8508 0.7699
-1.000 0.0266 0.03096 0.02418 -0.0652 0.8454 0.7903
-0.750 0.0361 0.03131 0.02449 -0.0619 0.8375 0.8086
-0.500 0.0541 0.03146 0.02461 -0.0597 0.8310 0.8262
-0.250 0.0849 0.03154 0.02462 -0.0590 0.8271 0.8444
0.000 0.0800 0.03173 0.02482 -0.0539 0.8164 0.8605
0.250 0.1084 0.03171 0.02474 -0.0532 0.8121 0.8783
0.500 0.1097 0.03193 0.02496 -0.0495 0.8024 0.8932
0.750 0.1427 0.03196 0.02490 -0.0504 0.7974 0.9060
1.000 0.1551 0.03226 0.02518 -0.0488 0.7888 0.9198
1.250 0.1865 0.03239 0.02527 -0.0498 0.7829 0.9332
1.500 0.2361 0.03245 0.02528 -0.0535 0.7796 0.9454
1.750 0.2567 0.03311 0.02597 -0.0546 0.7690 0.9610
2.000 0.3149 0.03335 0.02618 -0.0604 0.7652 0.9736
2.250 0.3379 0.03412 0.02694 -0.0619 0.7554 1.0000
2.500 0.3751 0.03440 0.02718 -0.0643 0.7502 1.0000
2.750 0.4227 0.03450 0.02725 -0.0676 0.7471 1.0000
3.000 0.4284 0.03552 0.02825 -0.0665 0.7352 1.0000
3.250 0.4760 0.03554 0.02827 -0.0696 0.7321 1.0000
3.500 0.4846 0.03663 0.02936 -0.0688 0.7204 1.0000
3.750 0.5317 0.03654 0.02927 -0.0717 0.7169 1.0000
4.000 0.5431 0.03762 0.03036 -0.0711 0.7055 1.0000
4.250 0.5903 0.03736 0.03013 -0.0737 0.7017 1.0000
4.500 0.6036 0.03838 0.03117 -0.0732 0.6903 1.0000
4.750 0.6523 0.03786 0.03070 -0.0756 0.6866 1.0000
5.000 0.6672 0.03875 0.03163 -0.0751 0.6749 1.0000
5.250 0.7228 0.03748 0.03043 -0.0777 0.6714 1.0000
5.500 0.7426 0.03786 0.03086 -0.0771 0.6591 1.0000
5.750 0.8038 0.03577 0.02888 -0.0796 0.6563 1.0000
6.000 0.8211 0.03627 0.02944 -0.0787 0.6439 1.0000
6.250 0.8821 0.03389 0.02721 -0.0810 0.6417 1.0000
6.500 0.9450 0.03131 0.02479 -0.0836 0.6400 1.0000
6.750 0.9639 0.03132 0.02490 -0.0822 0.6276 1.0000
7.000 0.9952 0.03057 0.02425 -0.0819 0.6176 1.0000
7.250 1.0708 0.02708 0.02096 -0.0859 0.6123 1.0000
7.500 1.1242 0.02479 0.01878 -0.0875 0.5973 1.0000
7.750 1.1697 0.02303 0.01705 -0.0883 0.5760 1.0000
8.000 1.1932 0.02257 0.01662 -0.0867 0.5508 1.0000
8.250 1.2117 0.02242 0.01646 -0.0846 0.5234 1.0000
8.500 1.2243 0.02253 0.01652 -0.0816 0.4923 1.0000
8.750 1.2308 0.02297 0.01686 -0.0780 0.4574 1.0000
9.000 1.2331 0.02370 0.01744 -0.0740 0.4177 1.0000
9.250 1.2308 0.02483 0.01830 -0.0700 0.3735 1.0000
9.500 1.2260 0.02637 0.01953 -0.0661 0.3287 1.0000
9.750 1.2211 0.02819 0.02103 -0.0626 0.2883 1.0000
10.000 1.2164 0.03021 0.02275 -0.0595 0.2525 1.0000
10.250 1.2122 0.03237 0.02463 -0.0566 0.2203 1.0000
10.500 1.2091 0.03463 0.02664 -0.0540 0.1906 1.0000
10.750 1.2094 0.03683 0.02862 -0.0518 0.1654 1.0000
11.000 1.2129 0.03889 0.03050 -0.0500 0.1461 1.0000
11.250 1.2205 0.04079 0.03225 -0.0484 0.1307 1.0000
11.500 1.2313 0.04254 0.03396 -0.0471 0.1183 1.0000
11.750 1.2457 0.04423 0.03563 -0.0460 0.1082 1.0000
12.000 1.2661 0.04581 0.03708 -0.0454 0.0999 1.0000
12.250 1.2801 0.04750 0.03890 -0.0444 0.0931 1.0000
12.500 1.3074 0.04923 0.04058 -0.0442 0.0865 1.0000
12.750 1.3207 0.05115 0.04268 -0.0432 0.0816 1.0000
13.000 1.3577 0.05323 0.04462 -0.0438 0.0760 1.0000
13.250 1.3643 0.05565 0.04740 -0.0424 0.0734 1.0000
13.500 1.3732 0.05811 0.05011 -0.0413 0.0705 1.0000
13.750 1.3829 0.06046 0.05256 -0.0405 0.0677 1.0000
14.000 1.4076 0.06417 0.05633 -0.0407 0.0647 1.0000
14.250 1.3972 0.06746 0.05999 -0.0389 0.0640 1.0000
14.500 1.3848 0.07112 0.06400 -0.0373 0.0633 1.0000
14.750 1.3699 0.07518 0.06841 -0.0361 0.0627 1.0000
15.000 1.3522 0.07961 0.07316 -0.0353 0.0621 1.0000
15.250 1.3322 0.08448 0.07833 -0.0350 0.0617 1.0000
15.500 1.3092 0.08989 0.08404 -0.0354 0.0615 1.0000
15.750 1.2836 0.09601 0.09044 -0.0366 0.0616 1.0000
16.000 1.2551 0.10297 0.09767 -0.0387 0.0619 1.0000
16.250 1.2239 0.11090 0.10585 -0.0420 0.0624 1.0000
16.500 1.1918 0.11983 0.11499 -0.0465 0.0632 1.0000
16.750 1.1596 0.12977 0.12510 -0.0522 0.0640 1.0000
17.000 1.1318 0.14006 0.13550 -0.0582 0.0648 1.0000
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