FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 76-MP-120 (fx76mp120-il) Reynolds number: 200,000 Max Cl/Cd: 85.94 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp120-il-200000.txt Download as CSV file: xf-fx76mp120-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 76-MP-120
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
------ -------- --------- --------- -------- -------- --------
-10.250 0.1793 0.09609 0.09191 -0.1569 0.9157 0.0402
-10.000 0.1925 0.09350 0.08930 -0.1597 0.9123 0.0420
-9.750 0.1961 0.09232 0.08811 -0.1637 0.9076 0.0439
-9.500 0.1921 0.09148 0.08731 -0.1647 0.9015 0.0442
-9.250 0.1962 0.08968 0.08550 -0.1672 0.8969 0.0443
-9.000 0.2150 0.08448 0.08028 -0.1672 0.8953 0.0451
-8.750 0.2329 0.08160 0.07737 -0.1672 0.8930 0.0461
-8.500 0.2358 0.08009 0.07589 -0.1656 0.8884 0.0469
-8.250 0.2425 0.07825 0.07406 -0.1653 0.8842 0.0484
-8.000 0.2505 0.07625 0.07205 -0.1662 0.8808 0.0501
-7.750 0.2524 0.07461 0.07043 -0.1668 0.8769 0.0525
-7.500 0.2406 0.07411 0.07001 -0.1649 0.8704 0.0535
-7.250 0.2265 0.07374 0.06969 -0.1655 0.8647 0.0542
-7.000 0.2174 0.07285 0.06885 -0.1658 0.8590 0.0544
-6.750 0.2155 0.07114 0.06717 -0.1673 0.8532 0.0545
-6.500 0.2258 0.06740 0.06345 -0.1614 0.8518 0.0560
-6.250 0.2419 0.06569 0.06171 -0.1600 0.8497 0.0583
-6.000 0.2478 0.06414 0.06016 -0.1603 0.8461 0.0606
-5.750 0.2321 0.06392 0.06003 -0.1565 0.8386 0.0620
-5.500 0.2587 0.05951 0.05539 -0.1749 0.8334 0.0664
-5.000 0.2406 0.05615 0.05217 -0.1662 0.8214 0.0678
-4.750 0.2585 0.05437 0.05040 -0.1650 0.8195 0.0697
-4.500 0.2880 0.05156 0.04751 -0.1688 0.8179 0.0730
-4.250 0.2537 0.05280 0.04883 -0.1598 0.8066 0.0729
-4.000 0.3056 0.04647 0.04210 -0.1729 0.8046 0.0820
-3.750 0.3632 0.03781 0.03271 -0.1837 0.8036 0.0653
-3.500 0.4140 0.03098 0.02513 -0.1913 0.8028 0.0589
-3.250 0.3627 0.04081 0.03600 -0.1755 0.7909 0.0974
-3.000 0.4035 0.03793 0.03295 -0.1794 0.7896 0.1001
-2.750 0.4814 0.02757 0.02064 -0.1906 0.7898 0.0682
-2.500 0.5189 0.02671 0.01970 -0.1925 0.7885 0.0741
-2.250 0.5587 0.02587 0.01853 -0.1943 0.7874 0.0803
-2.000 0.5509 0.02651 0.01920 -0.1889 0.7780 0.0827
-1.750 0.5829 0.02595 0.01858 -0.1897 0.7756 0.0889
-1.500 0.6199 0.02517 0.01765 -0.1912 0.7741 0.0973
-1.250 0.6580 0.02448 0.01693 -0.1928 0.7729 0.1069
-1.000 0.6968 0.02372 0.01617 -0.1947 0.7719 0.1189
-0.750 0.6857 0.02503 0.01750 -0.1885 0.7614 0.1226
-0.500 0.7215 0.02446 0.01695 -0.1898 0.7597 0.1389
-0.250 0.7598 0.02378 0.01633 -0.1915 0.7584 0.1617
0.000 0.7997 0.02306 0.01574 -0.1935 0.7574 0.2013
0.250 0.8390 0.02218 0.01528 -0.1957 0.7563 0.3206
0.500 0.8288 0.02302 0.01673 -0.1898 0.7456 0.5023
0.750 0.8565 0.02176 0.01632 -0.1884 0.7441 1.0000
1.000 0.8969 0.02134 0.01573 -0.1903 0.7428 1.0000
1.250 0.9370 0.02094 0.01517 -0.1922 0.7416 1.0000
1.500 0.9777 0.02054 0.01464 -0.1943 0.7405 1.0000
1.750 0.9726 0.02172 0.01584 -0.1891 0.7298 1.0000
2.000 1.0123 0.02125 0.01527 -0.1909 0.7283 1.0000
2.250 1.0529 0.02077 0.01470 -0.1929 0.7270 1.0000
2.500 1.0947 0.02026 0.01410 -0.1952 0.7258 1.0000
2.750 1.0912 0.02129 0.01518 -0.1901 0.7153 1.0000
3.000 1.1314 0.02076 0.01459 -0.1920 0.7136 1.0000
3.250 1.1731 0.02020 0.01396 -0.1942 0.7121 1.0000
3.500 1.1767 0.02095 0.01475 -0.1902 0.7030 1.0000
3.750 1.2143 0.02046 0.01423 -0.1917 0.7003 1.0000
4.000 1.2565 0.01981 0.01354 -0.1940 0.6981 1.0000
4.250 1.2717 0.02010 0.01385 -0.1918 0.6911 1.0000
4.500 1.3013 0.01984 0.01360 -0.1920 0.6863 1.0000
4.750 1.3431 0.01922 0.01294 -0.1942 0.6835 1.0000
5.000 1.3585 0.01945 0.01321 -0.1920 0.6761 1.0000
5.250 1.3900 0.01912 0.01289 -0.1925 0.6709 1.0000
5.500 1.4331 0.01850 0.01224 -0.1951 0.6674 1.0000
5.750 1.4400 0.01889 0.01270 -0.1913 0.6579 1.0000
6.000 1.4805 0.01836 0.01215 -0.1934 0.6532 1.0000
6.250 1.4895 0.01866 0.01253 -0.1900 0.6436 1.0000
6.500 1.5302 0.01816 0.01199 -0.1922 0.6378 1.0000
6.750 1.5367 0.01849 0.01239 -0.1883 0.6272 1.0000
7.000 1.5580 0.01849 0.01240 -0.1870 0.6184 1.0000
7.250 1.5828 0.01842 0.01235 -0.1863 0.6093 1.0000
7.500 1.5911 0.01877 0.01274 -0.1828 0.5984 1.0000
7.750 1.6092 0.01893 0.01291 -0.1811 0.5878 1.0000
8.000 1.6328 0.01900 0.01297 -0.1803 0.5771 1.0000
8.250 1.6434 0.01939 0.01338 -0.1774 0.5648 1.0000
8.500 1.6522 0.01990 0.01391 -0.1743 0.5521 1.0000
8.750 1.6634 0.02042 0.01445 -0.1716 0.5394 1.0000
9.000 1.6756 0.02096 0.01499 -0.1692 0.5267 1.0000
9.250 1.6877 0.02155 0.01558 -0.1669 0.5138 1.0000
9.500 1.6982 0.02223 0.01624 -0.1644 0.5003 1.0000
9.750 1.7088 0.02296 0.01695 -0.1620 0.4870 1.0000
10.000 1.7154 0.02387 0.01786 -0.1591 0.4730 1.0000
10.250 1.7200 0.02492 0.01893 -0.1561 0.4590 1.0000
10.500 1.7248 0.02603 0.02007 -0.1532 0.4451 1.0000
10.750 1.7291 0.02722 0.02129 -0.1504 0.4310 1.0000
11.000 1.7320 0.02852 0.02259 -0.1475 0.4162 1.0000
11.250 1.7333 0.02996 0.02403 -0.1445 0.4009 1.0000
11.500 1.7335 0.03154 0.02559 -0.1415 0.3852 1.0000
11.750 1.7319 0.03327 0.02729 -0.1385 0.3687 1.0000
12.000 1.7295 0.03516 0.02914 -0.1356 0.3520 1.0000
12.250 1.7271 0.03715 0.03111 -0.1328 0.3356 1.0000
12.500 1.7246 0.03927 0.03323 -0.1303 0.3194 1.0000
12.750 1.7228 0.04145 0.03543 -0.1279 0.3038 1.0000
13.000 1.7213 0.04371 0.03770 -0.1257 0.2884 1.0000
13.250 1.7191 0.04612 0.04011 -0.1237 0.2728 1.0000
13.500 1.7166 0.04866 0.04266 -0.1217 0.2573 1.0000
13.750 1.7138 0.05134 0.04535 -0.1199 0.2418 1.0000
14.000 1.7106 0.05416 0.04817 -0.1183 0.2263 1.0000
14.250 1.7067 0.05715 0.05116 -0.1167 0.2106 1.0000
14.500 1.7016 0.06037 0.05437 -0.1153 0.1944 1.0000
14.750 1.6952 0.06385 0.05784 -0.1140 0.1779 1.0000
15.000 1.6869 0.06768 0.06164 -0.1129 0.1611 1.0000
15.250 1.6793 0.07155 0.06551 -0.1119 0.1419 1.0000
15.500 1.6664 0.07620 0.07007 -0.1111 0.1215 1.0000
15.750 1.6520 0.08123 0.07500 -0.1106 0.0985 1.0000
16.000 1.6338 0.08693 0.08058 -0.1103 0.0762 1.0000
16.250 1.6146 0.09294 0.08648 -0.1103 0.0593 1.0000
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Polar data table (+)
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