FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 76-MP-120 (fx76mp120-il) Reynolds number: 1,000,000 Max Cl/Cd: 192.61 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp120-il-1000000.txt Download as CSV file: xf-fx76mp120-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.2024 0.08474 0.08194 -0.1471 0.7975 0.0137
-11.000 0.2090 0.08192 0.07913 -0.1480 0.7959 0.0140
-10.750 0.2088 0.07788 0.07510 -0.1497 0.7942 0.0150
-10.500 0.2143 0.07492 0.07213 -0.1507 0.7924 0.0150
-10.250 0.2175 0.07137 0.06859 -0.1518 0.7906 0.0151
-10.000 0.1738 0.08553 0.08260 -0.1563 0.7976 0.0151
-9.750 0.1813 0.08231 0.07939 -0.1581 0.7957 0.0151
-9.500 0.1911 0.07965 0.07674 -0.1596 0.7936 0.0151
-9.250 0.1987 0.07677 0.07386 -0.1605 0.7917 0.0156
-9.000 -0.0306 0.02023 0.01656 -0.2057 0.7820 0.0122
-8.750 -0.0087 0.01833 0.01445 -0.2071 0.7800 0.0126
-8.500 0.0165 0.01739 0.01340 -0.2078 0.7782 0.0129
-8.250 0.0429 0.01690 0.01283 -0.2082 0.7763 0.0134
-8.000 0.0690 0.01605 0.01184 -0.2088 0.7745 0.0139
-7.750 0.0958 0.01527 0.01088 -0.2094 0.7725 0.0144
-7.500 0.1232 0.01448 0.00989 -0.2100 0.7703 0.0148
-7.250 0.1500 0.01392 0.00923 -0.2103 0.7689 0.0151
-7.000 0.1758 0.01248 0.00756 -0.2109 0.7671 0.0160
-6.750 0.2033 0.01205 0.00707 -0.2112 0.7652 0.0165
-6.500 0.2312 0.01173 0.00670 -0.2114 0.7633 0.0173
-6.250 0.2592 0.01136 0.00624 -0.2117 0.7614 0.0180
-6.000 0.2873 0.01105 0.00584 -0.2119 0.7596 0.0187
-5.750 0.3154 0.01052 0.00520 -0.2122 0.7577 0.0198
-5.500 0.3442 0.01032 0.00495 -0.2126 0.7554 0.0210
-5.250 0.3719 0.01011 0.00472 -0.2127 0.7538 0.0223
-5.000 0.3998 0.00990 0.00447 -0.2128 0.7519 0.0234
-4.750 0.4276 0.00949 0.00401 -0.2130 0.7499 0.0253
-4.500 0.4558 0.00935 0.00386 -0.2131 0.7478 0.0273
-4.250 0.4841 0.00928 0.00376 -0.2132 0.7458 0.0291
-4.000 0.5123 0.00897 0.00342 -0.2135 0.7438 0.0322
-3.750 0.5410 0.00891 0.00331 -0.2137 0.7414 0.0347
-3.500 0.5690 0.00877 0.00315 -0.2138 0.7392 0.0370
-3.250 0.5966 0.00858 0.00298 -0.2138 0.7370 0.0405
-3.000 0.6244 0.00850 0.00290 -0.2139 0.7345 0.0434
-2.750 0.6524 0.00834 0.00271 -0.2140 0.7321 0.0470
-2.500 0.6803 0.00824 0.00262 -0.2141 0.7297 0.0511
-2.250 0.7087 0.00822 0.00255 -0.2142 0.7273 0.0543
-2.000 0.7369 0.00809 0.00243 -0.2144 0.7248 0.0608
-1.750 0.7642 0.00802 0.00237 -0.2143 0.7224 0.0654
-1.500 0.7917 0.00790 0.00228 -0.2143 0.7196 0.0732
-1.250 0.8193 0.00785 0.00223 -0.2143 0.7167 0.0797
-1.000 0.8469 0.00776 0.00216 -0.2144 0.7138 0.0912
-0.750 0.8751 0.00774 0.00213 -0.2145 0.7107 0.1039
-0.500 0.9019 0.00766 0.00211 -0.2144 0.7079 0.1191
-0.250 0.9290 0.00759 0.00209 -0.2143 0.7046 0.1405
0.000 0.9560 0.00750 0.00209 -0.2143 0.7013 0.1760
0.250 0.9832 0.00742 0.00209 -0.2143 0.6981 0.2250
0.500 1.0100 0.00730 0.00214 -0.2143 0.6948 0.3021
0.750 1.0359 0.00708 0.00221 -0.2141 0.6910 0.4235
1.000 1.0600 0.00670 0.00234 -0.2137 0.6873 0.6592
1.250 1.0838 0.00659 0.00245 -0.2128 0.6834 0.7817
1.500 1.1083 0.00658 0.00252 -0.2121 0.6794 0.8266
1.750 1.1322 0.00654 0.00257 -0.2112 0.6747 0.8642
2.000 1.1552 0.00651 0.00259 -0.2102 0.6700 0.9009
2.250 1.1890 0.00645 0.00260 -0.2116 0.6654 1.0000
2.500 1.2156 0.00651 0.00265 -0.2115 0.6602 1.0000
2.750 1.2414 0.00659 0.00269 -0.2112 0.6546 1.0000
3.000 1.2672 0.00668 0.00276 -0.2109 0.6487 1.0000
3.250 1.2928 0.00676 0.00283 -0.2106 0.6423 1.0000
3.500 1.3175 0.00688 0.00290 -0.2101 0.6358 1.0000
3.750 1.3425 0.00697 0.00299 -0.2097 0.6285 1.0000
4.000 1.3662 0.00711 0.00310 -0.2089 0.6207 1.0000
4.250 1.3899 0.00724 0.00320 -0.2082 0.6117 1.0000
4.500 1.4126 0.00740 0.00333 -0.2074 0.6021 1.0000
4.750 1.4339 0.00759 0.00348 -0.2062 0.5921 1.0000
5.000 1.4557 0.00777 0.00363 -0.2051 0.5814 1.0000
5.250 1.4766 0.00797 0.00380 -0.2039 0.5709 1.0000
5.500 1.4951 0.00820 0.00399 -0.2022 0.5595 1.0000
5.750 1.5107 0.00847 0.00421 -0.1998 0.5474 1.0000
6.000 1.5266 0.00875 0.00446 -0.1976 0.5343 1.0000
6.250 1.5426 0.00906 0.00472 -0.1955 0.5209 1.0000
6.500 1.5585 0.00937 0.00501 -0.1933 0.5086 1.0000
6.750 1.5737 0.00973 0.00532 -0.1911 0.4963 1.0000
7.000 1.5872 0.01014 0.00570 -0.1886 0.4826 1.0000
7.250 1.6007 0.01060 0.00611 -0.1862 0.4700 1.0000
7.500 1.6134 0.01111 0.00658 -0.1837 0.4572 1.0000
7.750 1.6272 0.01163 0.00707 -0.1816 0.4438 1.0000
8.000 1.6405 0.01221 0.00763 -0.1794 0.4302 1.0000
8.250 1.6538 0.01285 0.00825 -0.1774 0.4170 1.0000
8.500 1.6669 0.01357 0.00893 -0.1754 0.4037 1.0000
8.750 1.6797 0.01436 0.00969 -0.1736 0.3904 1.0000
9.000 1.6913 0.01530 0.01058 -0.1716 0.3745 1.0000
9.250 1.6995 0.01650 0.01170 -0.1694 0.3539 1.0000
9.500 1.7049 0.01794 0.01301 -0.1669 0.3282 1.0000
9.750 1.7096 0.01946 0.01441 -0.1644 0.3048 1.0000
10.000 1.7144 0.02097 0.01581 -0.1619 0.2807 1.0000
10.250 1.7205 0.02242 0.01717 -0.1597 0.2625 1.0000
10.500 1.7258 0.02390 0.01858 -0.1574 0.2441 1.0000
10.750 1.7322 0.02532 0.01994 -0.1552 0.2280 1.0000
11.000 1.7360 0.02694 0.02147 -0.1528 0.2090 1.0000
11.250 1.7421 0.02840 0.02290 -0.1507 0.1959 1.0000
11.500 1.7452 0.03010 0.02451 -0.1483 0.1790 1.0000
11.750 1.7497 0.03174 0.02611 -0.1462 0.1654 1.0000
12.000 1.7497 0.03372 0.02800 -0.1437 0.1479 1.0000
12.250 1.7518 0.03559 0.02980 -0.1414 0.1330 1.0000
12.500 1.7527 0.03759 0.03175 -0.1391 0.1178 1.0000
12.750 1.7517 0.03978 0.03385 -0.1367 0.1008 1.0000
13.000 1.7489 0.04215 0.03614 -0.1343 0.0855 1.0000
13.250 1.7442 0.04474 0.03864 -0.1317 0.0692 1.0000
13.500 1.7402 0.04734 0.04117 -0.1294 0.0548 1.0000
13.750 1.7370 0.04993 0.04372 -0.1272 0.0440 1.0000
14.000 1.7327 0.05266 0.04641 -0.1251 0.0341 1.0000
14.250 1.7291 0.05539 0.04911 -0.1232 0.0258 1.0000
14.500 1.7268 0.05809 0.05182 -0.1214 0.0200 1.0000
14.750 1.7239 0.06091 0.05465 -0.1198 0.0153 1.0000
15.000 1.7214 0.06371 0.05748 -0.1182 0.0121 1.0000
15.250 1.7215 0.06633 0.06015 -0.1170 0.0104 1.0000
15.500 1.7186 0.06935 0.06323 -0.1157 0.0087 1.0000
15.750 1.7195 0.07201 0.06596 -0.1148 0.0079 1.0000
16.000 1.7172 0.07513 0.06913 -0.1138 0.0072 1.0000
16.250 1.7138 0.07840 0.07249 -0.1129 0.0066 1.0000
16.500 1.7143 0.08127 0.07544 -0.1123 0.0063 1.0000
16.750 1.7138 0.08434 0.07860 -0.1118 0.0060 1.0000
17.000 1.7127 0.08756 0.08190 -0.1114 0.0057 1.0000
17.250 1.7100 0.09105 0.08547 -0.1111 0.0054 1.0000
17.500 1.7069 0.09466 0.08917 -0.1110 0.0053 1.0000
17.750 1.6981 0.09916 0.09377 -0.1111 0.0050 1.0000
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