FX 76-MP-140 (fx76mp140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 76-MP-140 (fx76mp140-il) Reynolds number: 500,000 Max Cl/Cd: 138.22 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx76mp140-il-500000.txt Download as CSV file: xf-fx76mp140-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.1454 0.09918 0.09554 -0.1528 0.8254 0.0285
-11.250 0.1377 0.09453 0.09091 -0.1580 0.8234 0.0310
-11.000 0.1427 0.09086 0.08727 -0.1595 0.8217 0.0312
-10.750 0.1636 0.08956 0.08596 -0.1586 0.8200 0.0318
-10.500 0.1770 0.08773 0.08413 -0.1594 0.8182 0.0327
-10.250 0.1862 0.08521 0.08161 -0.1609 0.8163 0.0330
-10.000 0.1763 0.08017 0.07660 -0.1661 0.8138 0.0359
-9.750 0.1845 0.07702 0.07344 -0.1670 0.8120 0.0364
-9.500 0.2046 0.07609 0.07248 -0.1668 0.8104 0.0371
-9.250 0.2184 0.07421 0.07058 -0.1679 0.8082 0.0383
-9.000 0.0058 0.03517 0.03155 -0.1918 0.7999 0.0313
-8.750 0.0232 0.03482 0.03123 -0.1916 0.7978 0.0317
-8.500 0.0187 0.03069 0.02683 -0.1936 0.7950 0.0321
-8.000 0.0502 0.02743 0.02322 -0.1949 0.7908 0.0334
-7.750 0.0565 0.02344 0.01870 -0.1955 0.7887 0.0341
-7.500 0.0736 0.02128 0.01617 -0.1954 0.7865 0.0349
-7.250 0.0948 0.01979 0.01436 -0.1953 0.7843 0.0355
-7.000 0.1185 0.01868 0.01297 -0.1953 0.7821 0.0362
-6.750 0.1427 0.01752 0.01173 -0.1954 0.7802 0.0371
-6.500 0.1693 0.01703 0.01119 -0.1956 0.7785 0.0380
-6.250 0.1967 0.01659 0.01064 -0.1958 0.7767 0.0392
-6.000 0.2246 0.01611 0.01003 -0.1960 0.7750 0.0405
-5.750 0.2526 0.01578 0.00952 -0.1963 0.7732 0.0416
-5.500 0.2770 0.01496 0.00868 -0.1960 0.7714 0.0432
-5.250 0.3026 0.01465 0.00838 -0.1958 0.7692 0.0447
-5.000 0.3290 0.01435 0.00804 -0.1956 0.7668 0.0466
-4.750 0.3561 0.01404 0.00764 -0.1955 0.7645 0.0486
-4.500 0.3835 0.01364 0.00726 -0.1956 0.7623 0.0513
-4.250 0.4121 0.01344 0.00701 -0.1958 0.7604 0.0540
-4.000 0.4409 0.01312 0.00662 -0.1961 0.7586 0.0567
-3.750 0.4699 0.01291 0.00640 -0.1965 0.7568 0.0597
-3.500 0.4961 0.01282 0.00631 -0.1963 0.7546 0.0628
-3.250 0.5217 0.01260 0.00608 -0.1959 0.7522 0.0659
-3.000 0.5480 0.01239 0.00591 -0.1957 0.7496 0.0697
-2.750 0.5756 0.01224 0.00574 -0.1957 0.7470 0.0736
-2.500 0.6040 0.01196 0.00545 -0.1959 0.7447 0.0786
-2.250 0.6332 0.01179 0.00526 -0.1962 0.7426 0.0840
-2.000 0.6628 0.01161 0.00507 -0.1966 0.7406 0.0913
-1.750 0.6895 0.01156 0.00503 -0.1965 0.7382 0.0996
-1.500 0.7144 0.01139 0.00495 -0.1960 0.7353 0.1116
-1.250 0.7408 0.01126 0.00487 -0.1958 0.7325 0.1278
-1.000 0.7686 0.01110 0.00476 -0.1958 0.7298 0.1505
-0.750 0.7974 0.01090 0.00463 -0.1961 0.7272 0.1813
-0.250 0.8531 0.01059 0.00455 -0.1964 0.7220 0.2790
0.000 0.8766 0.01035 0.00459 -0.1957 0.7185 0.3693
0.250 0.8996 0.00987 0.00465 -0.1951 0.7152 0.5700
0.500 0.9221 0.00958 0.00477 -0.1938 0.7122 0.7403
0.750 0.9488 0.00951 0.00473 -0.1933 0.7094 0.7913
1.000 0.9732 0.00950 0.00475 -0.1925 0.7059 0.8210
1.250 0.9947 0.00948 0.00478 -0.1911 0.7016 0.8427
1.500 1.0182 0.00942 0.00475 -0.1900 0.6977 0.8659
1.750 1.0429 0.00935 0.00468 -0.1892 0.6945 0.8887
2.000 1.0683 0.00930 0.00463 -0.1886 0.6911 0.9080
2.250 1.0893 0.00924 0.00465 -0.1872 0.6863 0.9341
2.500 1.1364 0.00917 0.00461 -0.1915 0.6820 0.9943
2.750 1.1599 0.00919 0.00456 -0.1907 0.6780 1.0000
3.000 1.1860 0.00925 0.00461 -0.1905 0.6730 1.0000
3.250 1.2105 0.00930 0.00466 -0.1899 0.6671 1.0000
3.500 1.2381 0.00933 0.00462 -0.1900 0.6619 1.0000
3.750 1.2616 0.00942 0.00472 -0.1893 0.6557 1.0000
4.000 1.2858 0.00949 0.00478 -0.1887 0.6493 1.0000
4.250 1.3117 0.00959 0.00482 -0.1884 0.6436 1.0000
4.500 1.3328 0.00970 0.00496 -0.1872 0.6359 1.0000
4.750 1.3573 0.00982 0.00500 -0.1867 0.6288 1.0000
5.000 1.3767 0.00996 0.00518 -0.1851 0.6196 1.0000
5.250 1.3970 0.01012 0.00529 -0.1838 0.6102 1.0000
5.500 1.4148 0.01030 0.00544 -0.1819 0.5995 1.0000
5.750 1.4304 0.01051 0.00564 -0.1796 0.5888 1.0000
6.000 1.4466 0.01077 0.00586 -0.1775 0.5782 1.0000
6.250 1.4621 0.01108 0.00612 -0.1753 0.5669 1.0000
6.500 1.4768 0.01143 0.00644 -0.1731 0.5545 1.0000
6.750 1.4908 0.01185 0.00683 -0.1708 0.5416 1.0000
7.000 1.5047 0.01232 0.00726 -0.1686 0.5296 1.0000
7.250 1.5184 0.01286 0.00775 -0.1665 0.5180 1.0000
7.500 1.5337 0.01340 0.00828 -0.1648 0.5067 1.0000
7.750 1.5483 0.01401 0.00888 -0.1631 0.4960 1.0000
8.250 1.5767 0.01543 0.01027 -0.1598 0.4734 1.0000
8.500 1.5907 0.01623 0.01105 -0.1583 0.4625 1.0000
8.750 1.6020 0.01720 0.01199 -0.1565 0.4501 1.0000
9.000 1.6146 0.01814 0.01292 -0.1549 0.4380 1.0000
9.250 1.6257 0.01921 0.01397 -0.1533 0.4242 1.0000
9.500 1.6362 0.02033 0.01507 -0.1516 0.4110 1.0000
9.750 1.6465 0.02147 0.01618 -0.1499 0.3995 1.0000
10.000 1.6564 0.02265 0.01735 -0.1482 0.3879 1.0000
10.250 1.6668 0.02381 0.01851 -0.1465 0.3757 1.0000
10.500 1.6756 0.02508 0.01976 -0.1448 0.3641 1.0000
10.750 1.6822 0.02650 0.02115 -0.1428 0.3510 1.0000
11.000 1.6873 0.02806 0.02266 -0.1407 0.3366 1.0000
11.250 1.6939 0.02954 0.02412 -0.1389 0.3234 1.0000
11.500 1.7007 0.03104 0.02561 -0.1371 0.3099 1.0000
11.750 1.7044 0.03281 0.02734 -0.1351 0.2941 1.0000
12.000 1.7090 0.03452 0.02902 -0.1332 0.2796 1.0000
12.250 1.7129 0.03635 0.03081 -0.1314 0.2658 1.0000
12.500 1.7171 0.03818 0.03261 -0.1296 0.2528 1.0000
12.750 1.7189 0.04025 0.03463 -0.1277 0.2384 1.0000
13.000 1.7205 0.04235 0.03667 -0.1258 0.2235 1.0000
13.250 1.7216 0.04456 0.03885 -0.1240 0.2107 1.0000
13.500 1.7236 0.04671 0.04097 -0.1224 0.1983 1.0000
13.750 1.7270 0.04879 0.04305 -0.1209 0.1873 1.0000
14.000 1.7294 0.05096 0.04520 -0.1194 0.1773 1.0000
14.250 1.7298 0.05337 0.04760 -0.1179 0.1682 1.0000
14.500 1.7333 0.05552 0.04976 -0.1166 0.1590 1.0000
14.750 1.7346 0.05793 0.05218 -0.1153 0.1515 1.0000
15.000 1.7363 0.06030 0.05457 -0.1141 0.1430 1.0000
15.250 1.7380 0.06271 0.05699 -0.1129 0.1350 1.0000
15.500 1.7357 0.06556 0.05984 -0.1116 0.1256 1.0000
15.750 1.7356 0.06822 0.06250 -0.1105 0.1162 1.0000
16.000 1.7323 0.07128 0.06555 -0.1094 0.1059 1.0000
16.250 1.7264 0.07466 0.06891 -0.1083 0.0933 1.0000
16.500 1.7152 0.07864 0.07282 -0.1071 0.0784 1.0000
16.750 1.7007 0.08310 0.07719 -0.1059 0.0620 1.0000
17.000 1.6854 0.08777 0.08180 -0.1050 0.0498 1.0000
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