FX 76-MP-160 (fx76mp160-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-160 (fx76mp160-il) Reynolds number: 200,000 Max Cl/Cd: 71.98 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp160-il-200000-n5.txt Download as CSV file: xf-fx76mp160-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 76-MP-160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2245 0.04237 0.03668 -0.1790 0.8390 0.0330
-11.500 -0.2501 0.03765 0.03177 -0.1815 0.8343 0.0330
-11.250 -0.2686 0.03461 0.02854 -0.1815 0.8300 0.0332
-11.000 -0.2810 0.03270 0.02646 -0.1798 0.8264 0.0333
-10.750 -0.2869 0.03106 0.02460 -0.1783 0.8235 0.0335
-10.500 -0.2829 0.02954 0.02279 -0.1773 0.8213 0.0339
-10.250 -0.2745 0.02843 0.02158 -0.1760 0.8189 0.0343
-10.000 -0.2623 0.02760 0.02071 -0.1748 0.8164 0.0347
-9.750 -0.2481 0.02678 0.01983 -0.1739 0.8140 0.0352
-9.500 -0.2322 0.02593 0.01889 -0.1730 0.8115 0.0359
-9.250 -0.2144 0.02510 0.01792 -0.1724 0.8091 0.0368
-9.000 -0.1948 0.02425 0.01689 -0.1720 0.8069 0.0379
-8.750 -0.1738 0.02343 0.01587 -0.1717 0.8051 0.0392
-8.500 -0.1515 0.02275 0.01518 -0.1715 0.8035 0.0403
-8.250 -0.1283 0.02217 0.01453 -0.1714 0.8020 0.0418
-8.000 -0.1093 0.02165 0.01393 -0.1705 0.7997 0.0433
-7.750 -0.0891 0.02113 0.01337 -0.1697 0.7974 0.0449
-7.500 -0.0670 0.02076 0.01301 -0.1692 0.7951 0.0465
-7.250 -0.0437 0.02041 0.01260 -0.1688 0.7928 0.0484
-7.000 -0.0192 0.02002 0.01214 -0.1685 0.7904 0.0503
-6.750 0.0070 0.01972 0.01180 -0.1685 0.7882 0.0524
-6.500 0.0342 0.01940 0.01139 -0.1686 0.7863 0.0548
-6.250 0.0619 0.01911 0.01102 -0.1689 0.7847 0.0572
-6.000 0.0898 0.01885 0.01069 -0.1691 0.7834 0.0599
-5.750 0.1104 0.01874 0.01053 -0.1680 0.7806 0.0625
-5.500 0.1324 0.01853 0.01035 -0.1673 0.7776 0.0651
-5.250 0.1566 0.01832 0.01010 -0.1668 0.7748 0.0683
-5.000 0.1822 0.01805 0.00982 -0.1666 0.7723 0.0718
-4.750 0.2092 0.01779 0.00956 -0.1667 0.7700 0.0760
-4.500 0.2375 0.01754 0.00932 -0.1669 0.7680 0.0813
-4.250 0.2670 0.01732 0.00908 -0.1674 0.7663 0.0875
-4.000 0.2972 0.01713 0.00883 -0.1679 0.7647 0.0955
-3.750 0.3178 0.01709 0.00885 -0.1667 0.7613 0.1022
-3.500 0.3395 0.01705 0.00883 -0.1658 0.7578 0.1090
-3.250 0.3643 0.01694 0.00874 -0.1653 0.7546 0.1167
-3.000 0.3913 0.01679 0.00863 -0.1653 0.7518 0.1267
-2.750 0.4200 0.01665 0.00846 -0.1655 0.7495 0.1390
-2.500 0.4502 0.01646 0.00825 -0.1659 0.7475 0.1498
-2.250 0.4815 0.01625 0.00806 -0.1666 0.7457 0.1618
-2.000 0.5030 0.01626 0.00815 -0.1656 0.7418 0.1749
-1.750 0.5226 0.01632 0.00824 -0.1642 0.7369 0.1897
-1.500 0.5482 0.01620 0.00816 -0.1638 0.7332 0.2052
-1.000 0.6069 0.01585 0.00791 -0.1645 0.7283 0.2481
-0.750 0.6387 0.01562 0.00774 -0.1653 0.7263 0.2711
-0.500 0.6550 0.01573 0.00797 -0.1633 0.7209 0.3006
-0.250 0.6765 0.01563 0.00801 -0.1622 0.7158 0.3323
0.000 0.7042 0.01537 0.00790 -0.1622 0.7121 0.3868
0.250 0.7349 0.01489 0.00771 -0.1628 0.7090 0.4767
0.500 0.7591 0.01464 0.00778 -0.1620 0.7053 0.5777
0.750 0.7698 0.01479 0.00824 -0.1585 0.6990 0.6540
1.000 0.7918 0.01480 0.00833 -0.1571 0.6945 0.7078
1.250 0.8202 0.01471 0.00821 -0.1569 0.6908 0.7393
1.500 0.8484 0.01464 0.00810 -0.1568 0.6868 0.7585
1.750 0.8564 0.01491 0.00845 -0.1530 0.6786 0.7717
2.000 0.8811 0.01484 0.00835 -0.1521 0.6728 0.7879
2.250 0.9065 0.01477 0.00824 -0.1514 0.6672 0.8007
2.500 0.9140 0.01496 0.00849 -0.1475 0.6589 0.8117
2.750 0.9394 0.01484 0.00835 -0.1467 0.6533 0.8233
3.000 0.9569 0.01491 0.00843 -0.1447 0.6465 0.8354
3.250 0.9728 0.01502 0.00853 -0.1423 0.6385 0.8485
3.500 1.0024 0.01482 0.00827 -0.1423 0.6318 0.8609
3.750 1.0081 0.01513 0.00863 -0.1382 0.6210 0.8718
4.000 1.0335 0.01505 0.00850 -0.1376 0.6118 0.8827
4.250 1.0452 0.01533 0.00879 -0.1348 0.6002 0.8953
4.500 1.0681 0.01536 0.00879 -0.1339 0.5899 0.9058
4.750 1.0905 0.01548 0.00886 -0.1331 0.5784 0.9185
5.250 1.1373 0.01580 0.00910 -0.1321 0.5555 1.0000
5.500 1.1542 0.01623 0.00950 -0.1306 0.5428 1.0000
5.750 1.1733 0.01662 0.00981 -0.1295 0.5302 1.0000
6.000 1.1916 0.01705 0.01013 -0.1282 0.5176 1.0000
6.250 1.2075 0.01759 0.01060 -0.1267 0.5047 1.0000
6.500 1.2236 0.01814 0.01105 -0.1252 0.4925 1.0000
6.750 1.2375 0.01878 0.01167 -0.1235 0.4795 1.0000
7.000 1.2519 0.01942 0.01226 -0.1219 0.4674 1.0000
7.250 1.2662 0.02009 0.01285 -0.1203 0.4561 1.0000
7.500 1.2802 0.02079 0.01352 -0.1187 0.4449 1.0000
7.750 1.2933 0.02155 0.01420 -0.1170 0.4340 1.0000
8.000 1.3066 0.02233 0.01499 -0.1154 0.4226 1.0000
8.250 1.3187 0.02317 0.01578 -0.1137 0.4111 1.0000
8.500 1.3302 0.02406 0.01663 -0.1120 0.3992 1.0000
8.750 1.3414 0.02499 0.01751 -0.1103 0.3876 1.0000
9.000 1.3533 0.02591 0.01839 -0.1087 0.3785 1.0000
9.250 1.3663 0.02680 0.01928 -0.1073 0.3689 1.0000
9.500 1.3787 0.02773 0.02020 -0.1059 0.3599 1.0000
9.750 1.3912 0.02868 0.02114 -0.1045 0.3513 1.0000
10.000 1.4033 0.02967 0.02214 -0.1031 0.3417 1.0000
10.250 1.4139 0.03076 0.02322 -0.1016 0.3329 1.0000
10.500 1.4238 0.03191 0.02435 -0.1002 0.3230 1.0000
10.750 1.4338 0.03309 0.02549 -0.0987 0.3151 1.0000
11.000 1.4466 0.03414 0.02659 -0.0976 0.3072 1.0000
11.250 1.4557 0.03543 0.02787 -0.0961 0.2987 1.0000
11.500 1.4679 0.03655 0.02903 -0.0951 0.2910 1.0000
11.750 1.4787 0.03778 0.03030 -0.0939 0.2832 1.0000
12.000 1.4875 0.03918 0.03169 -0.0926 0.2757 1.0000
12.250 1.4981 0.04048 0.03303 -0.0915 0.2684 1.0000
12.500 1.5051 0.04207 0.03460 -0.0902 0.2611 1.0000
12.750 1.5149 0.04348 0.03606 -0.0892 0.2543 1.0000
13.000 1.5250 0.04491 0.03753 -0.0882 0.2475 1.0000
13.250 1.5312 0.04666 0.03927 -0.0870 0.2408 1.0000
13.500 1.5417 0.04812 0.04083 -0.0862 0.2342 1.0000
13.750 1.5505 0.04973 0.04250 -0.0853 0.2274 1.0000
14.000 1.5562 0.05163 0.04441 -0.0843 0.2216 1.0000
14.250 1.5652 0.05328 0.04614 -0.0836 0.2159 1.0000
14.500 1.5717 0.05518 0.04808 -0.0827 0.2101 1.0000
14.750 1.5749 0.05742 0.05032 -0.0818 0.2047 1.0000
15.000 1.5833 0.05924 0.05225 -0.0812 0.1988 1.0000
15.250 1.5885 0.06139 0.05447 -0.0806 0.1927 1.0000
15.500 1.5899 0.06394 0.05702 -0.0798 0.1866 1.0000
15.750 1.5964 0.06604 0.05925 -0.0794 0.1800 1.0000
16.000 1.5981 0.06870 0.06196 -0.0789 0.1727 1.0000
16.250 1.5989 0.07151 0.06481 -0.0785 0.1661 1.0000
16.500 1.5992 0.07443 0.06778 -0.0782 0.1596 1.0000
16.750 1.5960 0.07781 0.07116 -0.0780 0.1541 1.0000
17.000 1.5999 0.08037 0.07384 -0.0779 0.1491 1.0000
17.250 1.6001 0.08343 0.07699 -0.0779 0.1436 1.0000
17.500 1.5980 0.08682 0.08042 -0.0779 0.1388 1.0000
17.750 1.5990 0.08987 0.08358 -0.0781 0.1342 1.0000
18.000 1.5989 0.09312 0.08693 -0.0784 0.1286 1.0000
18.250 1.5941 0.09703 0.09087 -0.0789 0.1234 1.0000
18.500 1.5916 0.10066 0.09458 -0.0795 0.1185 1.0000
18.750 1.5872 0.10459 0.09857 -0.0803 0.1136 1.0000
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Polar data table (+)
Polar graphs
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