FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 76-MP-120 (fx76mp120-il) Reynolds number: 500,000 Max Cl/Cd: 147.29 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp120-il-500000.txt Download as CSV file: xf-fx76mp120-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.2056 0.08761 0.08410 -0.1620 0.8340 0.0225
-9.750 0.2053 0.08470 0.08119 -0.1660 0.8309 0.0235
-9.500 0.2119 0.08212 0.07863 -0.1671 0.8283 0.0236
-9.250 0.2170 0.07870 0.07524 -0.1681 0.8258 0.0238
-9.000 0.2307 0.07646 0.07299 -0.1679 0.8235 0.0242
-8.750 0.2443 0.07472 0.07123 -0.1683 0.8212 0.0248
-8.500 0.2545 0.07259 0.06909 -0.1694 0.8189 0.0252
-8.250 0.2661 0.07062 0.06710 -0.1707 0.8163 0.0269
-8.000 0.2658 0.06811 0.06465 -0.1720 0.8135 0.0286
-7.750 0.2625 0.06521 0.06180 -0.1738 0.8099 0.0291
-7.500 0.2655 0.06273 0.05934 -0.1743 0.8069 0.0292
-7.250 0.2609 0.05930 0.05593 -0.1742 0.8041 0.0296
-7.000 0.2695 0.05725 0.05386 -0.1746 0.8018 0.0299
-6.750 0.2786 0.05558 0.05222 -0.1748 0.7993 0.0303
-6.500 0.2888 0.05417 0.05084 -0.1747 0.7966 0.0312
-6.250 0.2545 0.02085 0.01626 -0.2076 0.7901 0.0231
-6.000 0.2808 0.01793 0.01277 -0.2097 0.7881 0.0243
-5.750 0.3091 0.01765 0.01245 -0.2102 0.7863 0.0255
-5.500 0.3356 0.01690 0.01154 -0.2105 0.7842 0.0267
-5.250 0.3619 0.01591 0.01034 -0.2107 0.7819 0.0281
-5.000 0.3892 0.01530 0.00952 -0.2109 0.7795 0.0292
-4.750 0.4164 0.01436 0.00848 -0.2113 0.7772 0.0314
-4.500 0.4448 0.01409 0.00814 -0.2116 0.7752 0.0336
-4.250 0.4739 0.01375 0.00766 -0.2119 0.7733 0.0358
-4.000 0.5029 0.01303 0.00685 -0.2125 0.7715 0.0387
-3.750 0.5305 0.01291 0.00669 -0.2125 0.7693 0.0418
-3.500 0.5569 0.01287 0.00662 -0.2123 0.7668 0.0445
-3.250 0.5836 0.01232 0.00606 -0.2123 0.7641 0.0487
-3.000 0.6116 0.01218 0.00588 -0.2124 0.7617 0.0526
-2.750 0.6402 0.01183 0.00548 -0.2126 0.7594 0.0568
-2.500 0.6696 0.01167 0.00529 -0.2130 0.7573 0.0618
-2.250 0.6988 0.01162 0.00516 -0.2134 0.7551 0.0660
-2.000 0.7241 0.01132 0.00492 -0.2130 0.7522 0.0723
-1.750 0.7508 0.01124 0.00484 -0.2128 0.7493 0.0785
-1.500 0.7786 0.01102 0.00463 -0.2129 0.7466 0.0868
-1.250 0.8074 0.01092 0.00449 -0.2132 0.7441 0.0956
-1.000 0.8369 0.01077 0.00434 -0.2136 0.7419 0.1089
-0.750 0.8644 0.01069 0.00429 -0.2136 0.7393 0.1251
-0.500 0.8896 0.01056 0.00427 -0.2132 0.7358 0.1481
-0.250 0.9167 0.01040 0.00422 -0.2132 0.7325 0.1869
0.000 0.9449 0.01018 0.00417 -0.2135 0.7295 0.2615
0.250 0.9735 0.00986 0.00416 -0.2140 0.7269 0.4050
0.500 0.9956 0.00936 0.00440 -0.2130 0.7237 0.7031
0.750 1.0159 0.00922 0.00451 -0.2113 0.7198 0.8173
1.000 1.0384 0.00911 0.00448 -0.2099 0.7162 0.8737
1.250 1.0717 0.00889 0.00433 -0.2110 0.7132 0.9677
1.500 1.0996 0.00894 0.00432 -0.2111 0.7099 1.0000
1.750 1.1245 0.00899 0.00436 -0.2106 0.7055 1.0000
2.000 1.1517 0.00901 0.00435 -0.2106 0.7014 1.0000
2.250 1.1803 0.00903 0.00431 -0.2108 0.6977 1.0000
2.500 1.2060 0.00910 0.00436 -0.2105 0.6932 1.0000
2.750 1.2311 0.00914 0.00439 -0.2100 0.6880 1.0000
3.000 1.2584 0.00917 0.00438 -0.2100 0.6836 1.0000
3.250 1.2839 0.00924 0.00444 -0.2097 0.6785 1.0000
3.500 1.3081 0.00930 0.00450 -0.2090 0.6726 1.0000
3.750 1.3351 0.00936 0.00450 -0.2090 0.6675 1.0000
4.000 1.3576 0.00944 0.00463 -0.2080 0.6608 1.0000
4.250 1.3823 0.00952 0.00468 -0.2075 0.6545 1.0000
4.500 1.4057 0.00963 0.00479 -0.2067 0.6477 1.0000
4.750 1.4287 0.00973 0.00488 -0.2059 0.6402 1.0000
5.000 1.4509 0.00986 0.00503 -0.2048 0.6322 1.0000
5.250 1.4729 0.01000 0.00512 -0.2038 0.6235 1.0000
5.500 1.4931 0.01016 0.00530 -0.2024 0.6140 1.0000
5.750 1.5132 0.01034 0.00547 -0.2010 0.6047 1.0000
6.000 1.5318 0.01056 0.00567 -0.1993 0.5944 1.0000
6.250 1.5486 0.01078 0.00589 -0.1973 0.5839 1.0000
6.500 1.5631 0.01104 0.00614 -0.1948 0.5728 1.0000
6.750 1.5766 0.01136 0.00642 -0.1921 0.5609 1.0000
7.000 1.5890 0.01173 0.00676 -0.1893 0.5486 1.0000
7.250 1.6010 0.01212 0.00714 -0.1865 0.5357 1.0000
7.500 1.6131 0.01256 0.00756 -0.1838 0.5235 1.0000
7.750 1.6238 0.01307 0.00806 -0.1810 0.5107 1.0000
8.000 1.6337 0.01365 0.00862 -0.1781 0.4981 1.0000
8.250 1.6424 0.01433 0.00927 -0.1751 0.4848 1.0000
8.500 1.6507 0.01508 0.00999 -0.1722 0.4720 1.0000
8.750 1.6591 0.01590 0.01079 -0.1694 0.4584 1.0000
9.000 1.6678 0.01676 0.01164 -0.1668 0.4449 1.0000
9.250 1.6761 0.01770 0.01258 -0.1643 0.4314 1.0000
9.500 1.6844 0.01871 0.01358 -0.1619 0.4182 1.0000
9.750 1.6915 0.01983 0.01468 -0.1594 0.4041 1.0000
10.000 1.6968 0.02110 0.01591 -0.1568 0.3884 1.0000
10.250 1.7003 0.02253 0.01729 -0.1541 0.3710 1.0000
10.500 1.7025 0.02409 0.01878 -0.1513 0.3528 1.0000
10.750 1.7043 0.02573 0.02036 -0.1486 0.3337 1.0000
11.000 1.7064 0.02741 0.02198 -0.1460 0.3139 1.0000
11.250 1.7075 0.02921 0.02371 -0.1434 0.2948 1.0000
11.500 1.7081 0.03110 0.02552 -0.1409 0.2767 1.0000
11.750 1.7106 0.03291 0.02727 -0.1386 0.2592 1.0000
12.000 1.7129 0.03478 0.02910 -0.1364 0.2422 1.0000
12.250 1.7153 0.03670 0.03097 -0.1344 0.2256 1.0000
12.500 1.7179 0.03865 0.03288 -0.1324 0.2105 1.0000
12.750 1.7196 0.04072 0.03491 -0.1304 0.1952 1.0000
13.000 1.7213 0.04282 0.03698 -0.1286 0.1803 1.0000
13.250 1.7208 0.04520 0.03929 -0.1266 0.1643 1.0000
13.500 1.7195 0.04771 0.04174 -0.1248 0.1481 1.0000
13.750 1.7184 0.05024 0.04421 -0.1230 0.1320 1.0000
14.000 1.7157 0.05301 0.04692 -0.1213 0.1152 1.0000
14.250 1.7083 0.05634 0.05014 -0.1194 0.0955 1.0000
14.500 1.7022 0.05962 0.05334 -0.1178 0.0775 1.0000
14.750 1.6928 0.06337 0.05700 -0.1162 0.0603 1.0000
15.000 1.6843 0.06715 0.06072 -0.1149 0.0455 1.0000
15.250 1.6745 0.07124 0.06476 -0.1137 0.0336 1.0000
15.500 1.6661 0.07527 0.06878 -0.1128 0.0250 1.0000
15.750 1.6588 0.07929 0.07282 -0.1121 0.0199 1.0000
16.000 1.6529 0.08325 0.07684 -0.1116 0.0168 1.0000
16.250 1.6477 0.08723 0.08092 -0.1113 0.0148 1.0000
16.500 1.6433 0.09115 0.08493 -0.1111 0.0133 1.0000
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