FX 76-MP-140 (fx76mp140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-140 (fx76mp140-il) Reynolds number: 500,000 Max Cl/Cd: 131.52 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp140-il-500000-n5.txt Download as CSV file: xf-fx76mp140-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2910 0.03175 0.02755 -0.1866 0.7833 0.0191
-11.500 -0.3027 0.02728 0.02278 -0.1904 0.7804 0.0192
-11.250 -0.2956 0.02521 0.02053 -0.1910 0.7783 0.0195
-11.000 -0.2810 0.02384 0.01904 -0.1913 0.7763 0.0197
-10.750 -0.2615 0.02295 0.01803 -0.1915 0.7745 0.0201
-10.500 -0.2405 0.02213 0.01711 -0.1916 0.7728 0.0206
-10.250 -0.2199 0.02128 0.01616 -0.1917 0.7713 0.0211
-10.000 -0.1984 0.02046 0.01521 -0.1917 0.7697 0.0217
-9.750 -0.1765 0.01960 0.01418 -0.1917 0.7680 0.0223
-9.500 -0.1534 0.01882 0.01323 -0.1918 0.7663 0.0228
-9.250 -0.1297 0.01818 0.01255 -0.1918 0.7646 0.0234
-9.000 -0.1050 0.01763 0.01192 -0.1919 0.7629 0.0238
-8.750 -0.0798 0.01711 0.01131 -0.1919 0.7611 0.0244
-8.500 -0.0544 0.01656 0.01065 -0.1920 0.7595 0.0249
-8.250 -0.0284 0.01604 0.01000 -0.1921 0.7580 0.0255
-8.000 -0.0020 0.01553 0.00937 -0.1923 0.7566 0.0260
-7.750 0.0240 0.01505 0.00877 -0.1923 0.7550 0.0265
-7.500 0.0498 0.01458 0.00826 -0.1923 0.7533 0.0271
-7.250 0.0763 0.01423 0.00788 -0.1923 0.7514 0.0278
-7.000 0.1032 0.01395 0.00755 -0.1924 0.7496 0.0287
-6.750 0.1302 0.01364 0.00719 -0.1924 0.7478 0.0296
-6.500 0.1573 0.01331 0.00678 -0.1925 0.7459 0.0305
-6.250 0.1846 0.01298 0.00638 -0.1926 0.7442 0.0314
-6.000 0.2122 0.01271 0.00609 -0.1927 0.7426 0.0324
-5.750 0.2402 0.01250 0.00582 -0.1929 0.7410 0.0337
-5.500 0.2683 0.01229 0.00554 -0.1931 0.7393 0.0352
-5.250 0.2951 0.01205 0.00528 -0.1930 0.7375 0.0366
-5.000 0.3223 0.01186 0.00509 -0.1930 0.7356 0.0383
-4.750 0.3496 0.01169 0.00491 -0.1930 0.7334 0.0402
-4.500 0.3770 0.01151 0.00469 -0.1930 0.7310 0.0421
-4.250 0.4045 0.01131 0.00448 -0.1930 0.7287 0.0440
-4.000 0.4324 0.01116 0.00430 -0.1931 0.7266 0.0461
-3.750 0.4606 0.01104 0.00412 -0.1932 0.7246 0.0481
-3.500 0.4884 0.01089 0.00398 -0.1933 0.7227 0.0508
-3.250 0.5153 0.01078 0.00388 -0.1932 0.7203 0.0536
-3.000 0.5424 0.01068 0.00378 -0.1931 0.7178 0.0564
-2.750 0.5696 0.01055 0.00367 -0.1931 0.7152 0.0602
-2.500 0.5971 0.01045 0.00355 -0.1930 0.7124 0.0639
-2.250 0.6248 0.01032 0.00342 -0.1930 0.7099 0.0682
-2.000 0.6529 0.01024 0.00331 -0.1931 0.7076 0.0734
-1.750 0.6793 0.01016 0.00327 -0.1929 0.7048 0.0794
-1.500 0.7060 0.01009 0.00323 -0.1928 0.7017 0.0862
-1.250 0.7328 0.01001 0.00318 -0.1926 0.6987 0.0963
-1.000 0.7600 0.00993 0.00313 -0.1926 0.6959 0.1081
-0.750 0.7873 0.00986 0.00307 -0.1925 0.6928 0.1220
-0.500 0.8136 0.00981 0.00307 -0.1923 0.6894 0.1384
-0.250 0.8396 0.00975 0.00308 -0.1920 0.6854 0.1576
0.000 0.8658 0.00969 0.00307 -0.1918 0.6816 0.1820
0.250 0.8921 0.00960 0.00307 -0.1916 0.6781 0.2194
0.500 0.9181 0.00951 0.00309 -0.1914 0.6747 0.2685
0.750 0.9430 0.00941 0.00316 -0.1909 0.6701 0.3290
1.000 0.9674 0.00925 0.00320 -0.1904 0.6650 0.4145
1.250 0.9911 0.00903 0.00325 -0.1898 0.6604 0.5413
1.500 1.0116 0.00882 0.00346 -0.1883 0.6552 0.6992
1.750 1.0339 0.00881 0.00358 -0.1871 0.6502 0.7638
2.000 1.0576 0.00887 0.00363 -0.1862 0.6454 0.7904
2.250 1.0804 0.00892 0.00373 -0.1852 0.6398 0.8121
2.500 1.1029 0.00898 0.00381 -0.1841 0.6339 0.8308
2.750 1.1245 0.00904 0.00388 -0.1828 0.6283 0.8535
3.000 1.1453 0.00909 0.00398 -0.1814 0.6214 0.8767
3.250 1.1668 0.00911 0.00404 -0.1801 0.6139 0.9152
3.500 1.2047 0.00916 0.00414 -0.1825 0.6047 1.0000
3.750 1.2265 0.00934 0.00425 -0.1815 0.5959 1.0000
4.000 1.2479 0.00952 0.00440 -0.1804 0.5865 1.0000
4.250 1.2674 0.00972 0.00455 -0.1789 0.5781 1.0000
4.500 1.2856 0.00995 0.00474 -0.1771 0.5683 1.0000
4.750 1.3037 0.01020 0.00495 -0.1754 0.5578 1.0000
5.000 1.3204 0.01052 0.00520 -0.1734 0.5468 1.0000
5.250 1.3357 0.01088 0.00551 -0.1713 0.5343 1.0000
5.500 1.3515 0.01127 0.00585 -0.1693 0.5215 1.0000
5.750 1.3658 0.01174 0.00625 -0.1671 0.5079 1.0000
6.000 1.3798 0.01226 0.00672 -0.1650 0.4945 1.0000
6.250 1.3943 0.01282 0.00724 -0.1631 0.4831 1.0000
6.500 1.4086 0.01346 0.00782 -0.1613 0.4696 1.0000
6.750 1.4228 0.01415 0.00847 -0.1596 0.4557 1.0000
7.250 1.4513 0.01572 0.00996 -0.1566 0.4303 1.0000
7.500 1.4650 0.01661 0.01081 -0.1551 0.4184 1.0000
7.750 1.4820 0.01733 0.01153 -0.1541 0.4082 1.0000
8.000 1.4971 0.01819 0.01237 -0.1529 0.3986 1.0000
8.250 1.5114 0.01911 0.01327 -0.1517 0.3879 1.0000
8.500 1.5269 0.01997 0.01413 -0.1506 0.3785 1.0000
8.750 1.5394 0.02101 0.01514 -0.1491 0.3682 1.0000
9.000 1.5538 0.02194 0.01608 -0.1480 0.3583 1.0000
9.250 1.5648 0.02310 0.01721 -0.1464 0.3451 1.0000
9.500 1.5734 0.02442 0.01848 -0.1447 0.3310 1.0000
9.750 1.5821 0.02573 0.01975 -0.1429 0.3179 1.0000
10.000 1.5911 0.02704 0.02103 -0.1412 0.3059 1.0000
10.250 1.6035 0.02812 0.02212 -0.1399 0.2960 1.0000
10.500 1.6124 0.02947 0.02345 -0.1383 0.2851 1.0000
10.750 1.6204 0.03090 0.02485 -0.1367 0.2731 1.0000
11.000 1.6244 0.03267 0.02654 -0.1347 0.2560 1.0000
11.500 1.6374 0.03588 0.02969 -0.1313 0.2294 1.0000
11.750 1.6422 0.03767 0.03143 -0.1296 0.2151 1.0000
12.000 1.6445 0.03970 0.03339 -0.1277 0.1995 1.0000
12.250 1.6500 0.04149 0.03515 -0.1261 0.1875 1.0000
12.500 1.6552 0.04334 0.03699 -0.1246 0.1773 1.0000
12.750 1.6596 0.04528 0.03891 -0.1231 0.1675 1.0000
13.000 1.6633 0.04732 0.04092 -0.1216 0.1564 1.0000
13.250 1.6678 0.04932 0.04291 -0.1202 0.1470 1.0000
13.500 1.6711 0.05145 0.04502 -0.1188 0.1387 1.0000
13.750 1.6746 0.05358 0.04716 -0.1175 0.1289 1.0000
14.000 1.6775 0.05582 0.04939 -0.1162 0.1199 1.0000
14.250 1.6801 0.05812 0.05169 -0.1150 0.1126 1.0000
14.500 1.6814 0.06058 0.05414 -0.1137 0.1034 1.0000
14.750 1.6839 0.06294 0.05651 -0.1126 0.0952 1.0000
15.000 1.6814 0.06583 0.05939 -0.1113 0.0839 1.0000
15.250 1.6760 0.06907 0.06258 -0.1100 0.0710 1.0000
15.500 1.6675 0.07274 0.06619 -0.1087 0.0569 1.0000
15.750 1.6596 0.07640 0.06982 -0.1076 0.0468 1.0000
16.000 1.6545 0.07978 0.07321 -0.1066 0.0408 1.0000
16.250 1.6510 0.08305 0.07652 -0.1059 0.0364 1.0000
16.500 1.6488 0.08622 0.07974 -0.1053 0.0329 1.0000
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