WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 76-100 (fx76100-il) Reynolds number: 100,000 Max Cl/Cd: 35.37 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76100-il-100000.txt Download as CSV file: xf-fx76100-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-100
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.8152 0.07073 0.06523 -0.0347 1.0000 0.0727
-10.500 -0.8289 0.06607 0.06052 -0.0341 1.0000 0.0720
-10.250 -0.8484 0.06181 0.05612 -0.0323 1.0000 0.0714
-10.000 -0.8633 0.05743 0.05153 -0.0304 1.0000 0.0707
-9.750 -0.8753 0.05307 0.04688 -0.0282 1.0000 0.0701
-9.500 -0.8842 0.04883 0.04225 -0.0256 1.0000 0.0700
-9.250 -0.8876 0.04498 0.03796 -0.0229 1.0000 0.0704
-9.000 -0.8862 0.04186 0.03432 -0.0200 1.0000 0.0718
-8.750 -0.8819 0.03924 0.03114 -0.0170 1.0000 0.0733
-8.500 -0.8682 0.03587 0.02767 -0.0157 1.0000 0.0761
-8.250 -0.8524 0.03367 0.02526 -0.0140 1.0000 0.0785
-8.000 -0.8365 0.03184 0.02315 -0.0121 1.0000 0.0828
-7.750 -0.8206 0.02984 0.02072 -0.0100 1.0000 0.0869
-7.500 -0.7998 0.02791 0.01885 -0.0090 1.0000 0.0915
-7.250 -0.7805 0.02659 0.01726 -0.0073 1.0000 0.0980
-7.000 -0.7598 0.02496 0.01568 -0.0061 1.0000 0.1050
-6.750 -0.7391 0.02371 0.01420 -0.0046 1.0000 0.1135
-6.500 -0.7191 0.02252 0.01311 -0.0032 1.0000 0.1252
-6.250 -0.6995 0.02137 0.01202 -0.0016 1.0000 0.1395
-6.000 -0.6810 0.02031 0.01106 0.0001 1.0000 0.1587
-5.750 -0.6631 0.01942 0.01025 0.0020 1.0000 0.1859
-5.500 -0.6461 0.01856 0.00959 0.0039 1.0000 0.2181
-5.250 -0.6290 0.01787 0.00907 0.0059 1.0000 0.2521
-5.000 -0.6112 0.01729 0.00860 0.0078 1.0000 0.2850
-4.750 -0.5929 0.01676 0.00815 0.0096 1.0000 0.3160
-4.500 -0.5743 0.01625 0.00776 0.0114 1.0000 0.3468
-4.250 -0.5555 0.01576 0.00739 0.0131 1.0000 0.3784
-4.000 -0.5368 0.01528 0.00705 0.0150 1.0000 0.4134
-3.750 -0.5184 0.01478 0.00674 0.0169 1.0000 0.4515
-3.500 -0.5003 0.01429 0.00648 0.0189 1.0000 0.4955
-3.250 -0.4825 0.01381 0.00629 0.0211 1.0000 0.5458
-3.000 -0.4648 0.01338 0.00616 0.0235 1.0000 0.6052
-2.750 -0.4462 0.01303 0.00613 0.0260 1.0000 0.6707
-2.500 -0.4252 0.01285 0.00622 0.0283 1.0000 0.7396
-2.250 -0.3999 0.01289 0.00642 0.0301 1.0000 0.8059
-2.000 -0.3648 0.01314 0.00671 0.0300 1.0000 0.8617
-1.750 -0.3159 0.01354 0.00706 0.0271 1.0000 0.9056
-1.500 -0.2527 0.01400 0.00737 0.0211 1.0000 0.9358
-1.250 -0.1816 0.01435 0.00758 0.0132 1.0000 0.9574
-1.000 -0.1068 0.01448 0.00758 0.0042 1.0000 0.9748
-0.750 -0.0333 0.01437 0.00739 -0.0050 1.0000 0.9915
-0.500 0.0081 0.01414 0.00713 -0.0089 1.0000 1.0000
-0.250 0.0050 0.01400 0.00700 -0.0046 1.0000 1.0000
0.000 0.0000 0.01396 0.00696 0.0000 1.0000 1.0000
0.250 -0.0050 0.01400 0.00700 0.0046 1.0000 1.0000
0.500 -0.0081 0.01414 0.00713 0.0089 1.0000 1.0000
0.750 0.0330 0.01437 0.00739 0.0051 0.9916 1.0000
1.000 0.1070 0.01447 0.00758 -0.0042 0.9747 1.0000
1.250 0.1815 0.01435 0.00758 -0.0132 0.9576 1.0000
1.500 0.2531 0.01400 0.00738 -0.0211 0.9357 1.0000
1.750 0.3161 0.01354 0.00705 -0.0271 0.9053 1.0000
2.000 0.3648 0.01314 0.00671 -0.0300 0.8618 1.0000
2.250 0.3999 0.01289 0.00642 -0.0301 0.8058 1.0000
2.500 0.4252 0.01285 0.00622 -0.0283 0.7398 1.0000
2.750 0.4461 0.01303 0.00613 -0.0260 0.6707 1.0000
3.000 0.4647 0.01338 0.00616 -0.0235 0.6052 1.0000
3.250 0.4824 0.01381 0.00629 -0.0211 0.5458 1.0000
3.500 0.5002 0.01429 0.00648 -0.0189 0.4954 1.0000
3.750 0.5184 0.01478 0.00674 -0.0169 0.4514 1.0000
4.000 0.5368 0.01529 0.00704 -0.0149 0.4136 1.0000
4.250 0.5554 0.01576 0.00739 -0.0131 0.3785 1.0000
4.500 0.5742 0.01625 0.00776 -0.0113 0.3465 1.0000
4.750 0.5928 0.01676 0.00815 -0.0096 0.3158 1.0000
5.000 0.6111 0.01729 0.00859 -0.0078 0.2847 1.0000
5.250 0.6289 0.01786 0.00906 -0.0059 0.2520 1.0000
5.500 0.6461 0.01855 0.00959 -0.0039 0.2181 1.0000
5.750 0.6630 0.01941 0.01024 -0.0020 0.1858 1.0000
6.000 0.6808 0.02032 0.01106 -0.0001 0.1584 1.0000
6.250 0.6994 0.02138 0.01203 0.0016 0.1391 1.0000
6.500 0.7191 0.02254 0.01313 0.0032 0.1250 1.0000
6.750 0.7391 0.02373 0.01422 0.0046 0.1135 1.0000
7.000 0.7597 0.02496 0.01568 0.0062 0.1049 1.0000
7.250 0.7804 0.02658 0.01726 0.0074 0.0979 1.0000
7.500 0.7998 0.02792 0.01885 0.0090 0.0915 1.0000
7.750 0.8206 0.02984 0.02072 0.0101 0.0869 1.0000
8.000 0.8366 0.03189 0.02319 0.0121 0.0831 1.0000
8.250 0.8523 0.03370 0.02531 0.0140 0.0788 1.0000
8.500 0.8682 0.03589 0.02770 0.0157 0.0761 1.0000
8.750 0.8824 0.03892 0.03084 0.0171 0.0737 1.0000
9.000 0.8870 0.04199 0.03442 0.0199 0.0721 1.0000
9.250 0.8881 0.04508 0.03804 0.0228 0.0707 1.0000
9.500 0.8844 0.04888 0.04231 0.0256 0.0701 1.0000
9.750 0.8766 0.05304 0.04684 0.0281 0.0703 1.0000
10.000 0.8641 0.05744 0.05154 0.0304 0.0708 1.0000
10.250 0.8480 0.06189 0.05621 0.0322 0.0714 1.0000
10.500 0.8301 0.06608 0.06052 0.0340 0.0720 1.0000
10.750 0.8120 0.07076 0.06528 0.0346 0.0726 1.0000
11.000 0.8013 0.07614 0.07069 0.0341 0.0732 1.0000
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