FX 76-MP-140 (fx76mp140-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX 76-MP-140 (fx76mp140-il) Reynolds number: 200,000 Max Cl/Cd: 78.13 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp140-il-200000.txt Download as CSV file: xf-fx76mp140-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 76-MP-140
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
------ -------- --------- --------- -------- -------- --------
-11.250 0.1694 0.10094 0.09653 -0.1593 0.9015 0.0522
-11.000 0.1769 0.09845 0.09403 -0.1615 0.8982 0.0544
-10.750 0.1616 0.09677 0.09236 -0.1678 0.8938 0.0559
-10.500 0.1900 0.09277 0.08833 -0.1654 0.8923 0.0571
-10.250 0.1977 0.09081 0.08639 -0.1650 0.8892 0.0579
-10.000 0.2057 0.08885 0.08444 -0.1651 0.8860 0.0595
-9.750 0.2106 0.08681 0.08240 -0.1659 0.8828 0.0622
-9.500 0.1874 0.08582 0.08145 -0.1710 0.8776 0.0646
-9.250 0.2125 0.08175 0.07734 -0.1696 0.8763 0.0659
-9.000 0.2215 0.08009 0.07571 -0.1678 0.8733 0.0670
-8.750 0.2268 0.07852 0.07417 -0.1667 0.8699 0.0690
-8.500 0.2287 0.07684 0.07251 -0.1665 0.8662 0.0716
-8.250 0.2181 0.07515 0.07085 -0.1682 0.8618 0.0741
-8.000 0.1749 0.07498 0.07082 -0.1674 0.8548 0.0750
-7.750 0.1985 0.07126 0.06709 -0.1656 0.8533 0.0762
-7.500 0.2153 0.06969 0.06551 -0.1636 0.8507 0.0778
-7.250 0.2191 0.06818 0.06401 -0.1625 0.8471 0.0790
-7.000 0.2204 0.06662 0.06245 -0.1618 0.8440 0.0812
-6.750 0.2056 0.06593 0.06183 -0.1592 0.8393 0.0831
-6.500 0.1712 0.06456 0.06053 -0.1619 0.8304 0.0861
-6.250 0.1680 0.05923 0.05508 -0.1682 0.8266 0.0879
-6.000 0.1873 0.05779 0.05368 -0.1660 0.8252 0.0891
-5.750 0.1452 0.05897 0.05495 -0.1571 0.8141 0.0889
-5.500 0.1626 0.05730 0.05328 -0.1565 0.8116 0.0905
-5.250 0.1860 0.05495 0.05084 -0.1593 0.8097 0.0962
-5.000 0.1375 0.05695 0.05296 -0.1474 0.7978 0.0939
-4.750 0.1600 0.05123 0.04687 -0.1559 0.7942 0.1026
-4.500 0.1889 0.04926 0.04489 -0.1571 0.7929 0.1050
-4.250 0.1753 0.03489 0.02863 -0.1606 0.7818 0.0663
-4.000 0.2029 0.03434 0.02809 -0.1610 0.7790 0.0687
-3.750 0.2408 0.03257 0.02595 -0.1633 0.7777 0.0711
-3.500 0.2831 0.03090 0.02381 -0.1659 0.7767 0.0741
-3.250 0.3239 0.02951 0.02227 -0.1684 0.7758 0.0784
-3.000 0.2968 0.03101 0.02378 -0.1601 0.7643 0.0788
-2.750 0.3299 0.03039 0.02305 -0.1609 0.7620 0.0832
-2.500 0.3685 0.02940 0.02185 -0.1625 0.7606 0.0884
-2.250 0.4077 0.02863 0.02109 -0.1644 0.7596 0.0943
-2.000 0.4497 0.02797 0.02027 -0.1665 0.7588 0.1008
-1.750 0.4248 0.02947 0.02180 -0.1586 0.7467 0.1016
-1.500 0.5317 0.02626 0.01856 -0.1707 0.7574 0.1177
-1.250 0.4966 0.02812 0.02044 -0.1609 0.7435 0.1170
-1.000 0.5369 0.02737 0.01973 -0.1627 0.7427 0.1287
-0.750 0.5302 0.02853 0.02089 -0.1576 0.7333 0.1335
-0.500 0.5904 0.02692 0.01939 -0.1623 0.7365 0.1585
-0.250 0.6449 0.02574 0.01833 -0.1665 0.7378 0.2006
0.000 0.6970 0.02446 0.01740 -0.1705 0.7390 0.2909
0.500 0.6759 0.02616 0.01976 -0.1586 0.7189 0.4645
0.750 0.7162 0.02436 0.01890 -0.1585 0.7211 0.8425
1.000 0.7736 0.02324 0.01782 -0.1628 0.7219 1.0000
1.250 0.8281 0.02236 0.01677 -0.1670 0.7232 1.0000
1.500 0.8109 0.02379 0.01820 -0.1601 0.7106 1.0000
1.750 0.8545 0.02323 0.01752 -0.1625 0.7098 1.0000
2.000 0.9001 0.02260 0.01679 -0.1652 0.7091 1.0000
2.250 0.9454 0.02193 0.01602 -0.1679 0.7083 1.0000
2.500 0.9288 0.02322 0.01733 -0.1609 0.6961 1.0000
2.750 0.9725 0.02258 0.01661 -0.1632 0.6950 1.0000
3.000 1.0187 0.02189 0.01585 -0.1661 0.6941 1.0000
3.250 1.0641 0.02122 0.01512 -0.1689 0.6931 1.0000
3.500 1.1100 0.02057 0.01441 -0.1718 0.6920 1.0000
3.750 1.0931 0.02172 0.01560 -0.1644 0.6803 1.0000
4.000 1.1398 0.02099 0.01483 -0.1674 0.6788 1.0000
4.250 1.1877 0.02025 0.01404 -0.1706 0.6774 1.0000
4.500 1.1783 0.02107 0.01490 -0.1643 0.6670 1.0000
4.750 1.2233 0.02034 0.01414 -0.1670 0.6644 1.0000
5.000 1.2724 0.01958 0.01334 -0.1704 0.6621 1.0000
5.250 1.2725 0.02010 0.01389 -0.1656 0.6531 1.0000
5.500 1.3101 0.01963 0.01341 -0.1672 0.6488 1.0000
5.750 1.3616 0.01891 0.01265 -0.1712 0.6458 1.0000
6.000 1.3564 0.01952 0.01331 -0.1654 0.6357 1.0000
6.250 1.4026 0.01885 0.01260 -0.1684 0.6308 1.0000
6.500 1.4065 0.01929 0.01308 -0.1642 0.6212 1.0000
6.750 1.4477 0.01874 0.01248 -0.1663 0.6145 1.0000
7.000 1.4508 0.01920 0.01298 -0.1621 0.6035 1.0000
7.250 1.4774 0.01906 0.01281 -0.1618 0.5943 1.0000
7.500 1.4953 0.01923 0.01296 -0.1601 0.5842 1.0000
7.750 1.5071 0.01968 0.01343 -0.1577 0.5737 1.0000
8.000 1.5352 0.01965 0.01336 -0.1577 0.5641 1.0000
8.250 1.5452 0.02017 0.01388 -0.1550 0.5522 1.0000
8.500 1.5546 0.02080 0.01452 -0.1524 0.5404 1.0000
8.750 1.5720 0.02120 0.01489 -0.1509 0.5291 1.0000
9.000 1.5912 0.02158 0.01523 -0.1498 0.5181 1.0000
9.250 1.5965 0.02250 0.01620 -0.1468 0.5063 1.0000
9.500 1.6103 0.02317 0.01685 -0.1451 0.4953 1.0000
9.750 1.6292 0.02364 0.01727 -0.1440 0.4846 1.0000
10.000 1.6321 0.02478 0.01848 -0.1410 0.4728 1.0000
10.250 1.6423 0.02568 0.01939 -0.1390 0.4616 1.0000
10.500 1.6559 0.02642 0.02008 -0.1374 0.4503 1.0000
10.750 1.6606 0.02761 0.02131 -0.1348 0.4383 1.0000
11.000 1.6660 0.02883 0.02257 -0.1325 0.4263 1.0000
11.250 1.6722 0.03001 0.02374 -0.1302 0.4138 1.0000
11.500 1.6801 0.03113 0.02481 -0.1282 0.4017 1.0000
11.750 1.6817 0.03266 0.02640 -0.1257 0.3891 1.0000
12.000 1.6833 0.03425 0.02801 -0.1233 0.3758 1.0000
12.250 1.6848 0.03590 0.02966 -0.1209 0.3623 1.0000
12.500 1.6866 0.03760 0.03135 -0.1187 0.3491 1.0000
12.750 1.6870 0.03945 0.03317 -0.1165 0.3354 1.0000
13.000 1.6879 0.04136 0.03507 -0.1144 0.3223 1.0000
13.250 1.6874 0.04349 0.03723 -0.1124 0.3088 1.0000
13.500 1.6878 0.04561 0.03937 -0.1106 0.2959 1.0000
13.750 1.6876 0.04783 0.04161 -0.1088 0.2831 1.0000
14.000 1.6874 0.05012 0.04387 -0.1071 0.2713 1.0000
14.250 1.6868 0.05252 0.04627 -0.1055 0.2594 1.0000
14.500 1.6869 0.05495 0.04875 -0.1041 0.2481 1.0000
14.750 1.6867 0.05744 0.05125 -0.1028 0.2376 1.0000
15.250 1.6835 0.06290 0.05675 -0.1003 0.2163 1.0000
15.500 1.6821 0.06571 0.05960 -0.0993 0.2065 1.0000
15.750 1.6790 0.06871 0.06258 -0.0983 0.1974 1.0000
16.000 1.6776 0.07168 0.06565 -0.0975 0.1877 1.0000
16.250 1.6746 0.07484 0.06884 -0.0968 0.1789 1.0000
16.500 1.6712 0.07812 0.07217 -0.0962 0.1702 1.0000
16.750 1.6682 0.08144 0.07557 -0.0957 0.1614 1.0000
17.000 1.6615 0.08525 0.07939 -0.0954 0.1528 1.0000
17.250 1.6568 0.08893 0.08318 -0.0952 0.1430 1.0000
17.500 1.6492 0.09306 0.08737 -0.0952 0.1319 1.0000
17.750 1.6388 0.09766 0.09201 -0.0954 0.1196 1.0000
18.000 1.6250 0.10283 0.09717 -0.0958 0.1055 1.0000
18.250 1.6078 0.10859 0.10288 -0.0966 0.0903 1.0000
18.500 1.5910 0.11437 0.10861 -0.0976 0.0766 1.0000
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Polar data table (+)
Polar graphs
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