FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-120 (fx76mp120-il) Reynolds number: 200,000 Max Cl/Cd: 88.55 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp120-il-200000-n5.txt Download as CSV file: xf-fx76mp120-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.1584 0.09525 0.09043 -0.1555 0.8419 0.0291
-10.000 0.1647 0.09264 0.08783 -0.1567 0.8387 0.0292
-9.750 0.1723 0.08982 0.08500 -0.1577 0.8358 0.0292
-9.250 0.1928 0.08267 0.07779 -0.1590 0.8314 0.0235
-9.000 0.2024 0.08051 0.07565 -0.1587 0.8287 0.0230
-8.750 0.2097 0.07834 0.07350 -0.1589 0.8255 0.0225
-8.500 0.2156 0.07597 0.07113 -0.1595 0.8223 0.0221
-8.250 0.2206 0.07335 0.06851 -0.1603 0.8195 0.0219
-8.000 0.2260 0.07073 0.06589 -0.1612 0.8172 0.0217
-7.750 0.2273 0.06820 0.06340 -0.1615 0.8140 0.0218
-7.500 0.2279 0.06588 0.06113 -0.1613 0.8104 0.0216
-7.250 0.2252 0.06329 0.05858 -0.1614 0.8067 0.0225
-7.000 0.2221 0.06067 0.05598 -0.1617 0.8036 0.0227
-6.750 0.2237 0.05693 0.05224 -0.1648 0.8010 0.0232
-6.500 0.2212 0.05285 0.04822 -0.1679 0.7966 0.0234
-6.250 0.2270 0.04809 0.04344 -0.1732 0.7927 0.0234
-6.000 0.2365 0.02932 0.02391 -0.1941 0.7886 0.0240
-5.750 0.2636 0.02773 0.02210 -0.1962 0.7868 0.0249
-5.500 0.2904 0.02553 0.01954 -0.1984 0.7846 0.0267
-5.250 0.3161 0.02188 0.01508 -0.2006 0.7814 0.0290
-5.000 0.3420 0.02078 0.01379 -0.2011 0.7787 0.0302
-4.750 0.3690 0.02016 0.01303 -0.2015 0.7763 0.0317
-4.500 0.3975 0.01943 0.01206 -0.2020 0.7742 0.0343
-4.250 0.4268 0.01866 0.01105 -0.2027 0.7723 0.0371
-4.000 0.4565 0.01823 0.01054 -0.2033 0.7707 0.0395
-3.750 0.4804 0.01791 0.01010 -0.2028 0.7676 0.0426
-3.500 0.5053 0.01752 0.00963 -0.2025 0.7644 0.0459
-3.250 0.5319 0.01725 0.00933 -0.2024 0.7618 0.0490
-3.000 0.5598 0.01699 0.00895 -0.2026 0.7595 0.0535
-2.750 0.5889 0.01657 0.00848 -0.2030 0.7575 0.0574
-2.500 0.6189 0.01633 0.00818 -0.2035 0.7558 0.0624
-2.250 0.6419 0.01624 0.00805 -0.2027 0.7523 0.0670
-2.000 0.6663 0.01608 0.00792 -0.2023 0.7488 0.0722
-1.750 0.6932 0.01595 0.00775 -0.2022 0.7460 0.0791
-1.500 0.7218 0.01571 0.00752 -0.2024 0.7436 0.0865
-1.250 0.7518 0.01553 0.00727 -0.2029 0.7415 0.0960
-1.000 0.7767 0.01547 0.00724 -0.2025 0.7382 0.1070
-0.750 0.7996 0.01545 0.00729 -0.2017 0.7342 0.1192
-0.500 0.8261 0.01536 0.00722 -0.2016 0.7310 0.1372
-0.250 0.8549 0.01520 0.00710 -0.2019 0.7284 0.1617
0.000 0.8853 0.01499 0.00698 -0.2025 0.7262 0.2031
0.250 0.9065 0.01501 0.00717 -0.2015 0.7218 0.2572
0.500 0.9303 0.01484 0.00730 -0.2011 0.7177 0.3593
0.750 0.9547 0.01430 0.00743 -0.2005 0.7145 0.6186
1.000 0.9771 0.01395 0.00742 -0.1989 0.7119 0.8130
1.250 0.9950 0.01392 0.00751 -0.1967 0.7072 0.8947
1.750 1.0496 0.01392 0.00743 -0.1967 0.6990 1.0000
2.000 1.0807 0.01389 0.00729 -0.1973 0.6962 1.0000
2.250 1.0985 0.01417 0.00759 -0.1956 0.6899 1.0000
2.500 1.1246 0.01423 0.00760 -0.1953 0.6854 1.0000
2.750 1.1550 0.01419 0.00749 -0.1959 0.6820 1.0000
3.000 1.1733 0.01445 0.00777 -0.1942 0.6756 1.0000
3.250 1.1983 0.01453 0.00782 -0.1938 0.6705 1.0000
3.500 1.2273 0.01452 0.00776 -0.1940 0.6662 1.0000
3.750 1.2442 0.01479 0.00807 -0.1921 0.6589 1.0000
4.000 1.2715 0.01480 0.00803 -0.1921 0.6536 1.0000
4.250 1.2902 0.01502 0.00827 -0.1905 0.6462 1.0000
4.500 1.3145 0.01510 0.00834 -0.1899 0.6397 1.0000
4.750 1.3338 0.01530 0.00855 -0.1884 0.6322 1.0000
5.000 1.3559 0.01541 0.00864 -0.1874 0.6248 1.0000
5.250 1.3724 0.01565 0.00889 -0.1853 0.6163 1.0000
5.500 1.3955 0.01576 0.00898 -0.1845 0.6085 1.0000
5.750 1.4096 0.01608 0.00933 -0.1821 0.5988 1.0000
6.000 1.4290 0.01631 0.00955 -0.1807 0.5898 1.0000
6.250 1.4470 0.01659 0.00981 -0.1790 0.5797 1.0000
6.500 1.4616 0.01697 0.01021 -0.1769 0.5688 1.0000
6.750 1.4776 0.01735 0.01057 -0.1750 0.5577 1.0000
7.000 1.4934 0.01775 0.01095 -0.1731 0.5460 1.0000
7.250 1.5077 0.01823 0.01141 -0.1710 0.5341 1.0000
7.500 1.5202 0.01881 0.01200 -0.1687 0.5218 1.0000
7.750 1.5327 0.01943 0.01261 -0.1665 0.5096 1.0000
8.000 1.5450 0.02009 0.01326 -0.1643 0.4974 1.0000
8.250 1.5563 0.02082 0.01398 -0.1621 0.4847 1.0000
8.500 1.5671 0.02162 0.01476 -0.1598 0.4721 1.0000
8.750 1.5766 0.02250 0.01565 -0.1575 0.4590 1.0000
9.000 1.5860 0.02344 0.01660 -0.1552 0.4463 1.0000
9.250 1.5954 0.02442 0.01758 -0.1530 0.4339 1.0000
9.500 1.6042 0.02545 0.01862 -0.1508 0.4215 1.0000
9.750 1.6125 0.02655 0.01972 -0.1486 0.4093 1.0000
10.000 1.6199 0.02774 0.02092 -0.1464 0.3968 1.0000
10.250 1.6272 0.02897 0.02217 -0.1443 0.3839 1.0000
10.500 1.6342 0.03025 0.02348 -0.1421 0.3714 1.0000
10.750 1.6405 0.03162 0.02486 -0.1400 0.3588 1.0000
11.000 1.6466 0.03303 0.02629 -0.1379 0.3465 1.0000
11.250 1.6512 0.03458 0.02784 -0.1358 0.3339 1.0000
11.500 1.6548 0.03626 0.02954 -0.1337 0.3203 1.0000
11.750 1.6573 0.03809 0.03136 -0.1315 0.3055 1.0000
12.000 1.6580 0.04011 0.03337 -0.1294 0.2888 1.0000
12.250 1.6580 0.04229 0.03552 -0.1273 0.2718 1.0000
12.500 1.6568 0.04465 0.03784 -0.1253 0.2535 1.0000
12.750 1.6547 0.04719 0.04033 -0.1233 0.2355 1.0000
13.000 1.6523 0.04984 0.04294 -0.1215 0.2187 1.0000
13.250 1.6507 0.05251 0.04560 -0.1199 0.2026 1.0000
13.500 1.6497 0.05521 0.04829 -0.1185 0.1865 1.0000
13.750 1.6479 0.05806 0.05112 -0.1171 0.1708 1.0000
14.000 1.6453 0.06110 0.05413 -0.1158 0.1547 1.0000
14.250 1.6415 0.06434 0.05734 -0.1147 0.1383 1.0000
14.500 1.6367 0.06780 0.06076 -0.1137 0.1223 1.0000
14.750 1.6314 0.07141 0.06434 -0.1128 0.1062 1.0000
15.000 1.6252 0.07522 0.06811 -0.1120 0.0897 1.0000
15.250 1.6180 0.07925 0.07211 -0.1114 0.0746 1.0000
15.750 1.6023 0.08783 0.08065 -0.1108 0.0496 1.0000
16.000 1.5953 0.09213 0.08496 -0.1108 0.0408 1.0000
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