FX 76-MP-140 (fx76mp140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-140 (fx76mp140-il) Reynolds number: 1,000,000 Max Cl/Cd: 153.4 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp140-il-1000000-n5.txt Download as CSV file: xf-fx76mp140-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5178 0.02826 0.02447 -0.1890 0.7720 0.0136
-13.500 -0.5193 0.02496 0.02100 -0.1918 0.7702 0.0137
-13.250 -0.5082 0.02325 0.01917 -0.1925 0.7686 0.0139
-13.000 -0.4925 0.02199 0.01781 -0.1927 0.7670 0.0142
-12.750 -0.4742 0.02098 0.01670 -0.1928 0.7654 0.0146
-12.500 -0.4550 0.02002 0.01564 -0.1929 0.7637 0.0148
-12.250 -0.4339 0.01926 0.01477 -0.1929 0.7621 0.0152
-12.000 -0.4123 0.01852 0.01393 -0.1928 0.7604 0.0155
-11.750 -0.3897 0.01786 0.01316 -0.1928 0.7586 0.0158
-11.500 -0.3663 0.01727 0.01245 -0.1928 0.7567 0.0159
-11.250 -0.3430 0.01658 0.01168 -0.1928 0.7555 0.0163
-11.000 -0.3191 0.01593 0.01097 -0.1929 0.7544 0.0166
-10.750 -0.2942 0.01540 0.01039 -0.1929 0.7531 0.0170
-10.500 -0.2685 0.01499 0.00994 -0.1930 0.7517 0.0175
-10.250 -0.2428 0.01454 0.00942 -0.1930 0.7504 0.0178
-10.000 -0.2168 0.01414 0.00896 -0.1931 0.7489 0.0182
-9.750 -0.1905 0.01375 0.00850 -0.1932 0.7474 0.0186
-9.500 -0.1641 0.01340 0.00807 -0.1932 0.7457 0.0190
-9.250 -0.1375 0.01306 0.00766 -0.1933 0.7440 0.0193
-9.000 -0.1112 0.01263 0.00718 -0.1933 0.7425 0.0200
-8.750 -0.0843 0.01231 0.00681 -0.1934 0.7409 0.0205
-8.500 -0.0570 0.01206 0.00651 -0.1935 0.7393 0.0211
-8.250 -0.0297 0.01176 0.00618 -0.1936 0.7381 0.0216
-8.000 -0.0023 0.01147 0.00585 -0.1937 0.7366 0.0220
-7.750 0.0253 0.01119 0.00552 -0.1938 0.7350 0.0224
-7.500 0.0529 0.01094 0.00523 -0.1939 0.7334 0.0228
-7.250 0.0804 0.01064 0.00490 -0.1940 0.7316 0.0235
-7.000 0.1081 0.01041 0.00464 -0.1941 0.7298 0.0242
-6.750 0.1359 0.01021 0.00440 -0.1942 0.7281 0.0250
-6.500 0.1637 0.01003 0.00419 -0.1943 0.7264 0.0258
-6.250 0.1915 0.00986 0.00397 -0.1944 0.7246 0.0266
-6.000 0.2195 0.00968 0.00376 -0.1945 0.7229 0.0276
-5.750 0.2475 0.00951 0.00360 -0.1946 0.7214 0.0289
-5.500 0.2757 0.00936 0.00344 -0.1947 0.7195 0.0303
-5.250 0.3037 0.00921 0.00328 -0.1948 0.7171 0.0315
-5.000 0.3315 0.00906 0.00313 -0.1949 0.7146 0.0332
-4.750 0.3594 0.00895 0.00300 -0.1949 0.7123 0.0348
-4.500 0.3873 0.00886 0.00287 -0.1949 0.7102 0.0362
-4.250 0.4151 0.00874 0.00274 -0.1950 0.7080 0.0382
-4.000 0.4432 0.00864 0.00264 -0.1951 0.7061 0.0401
-3.750 0.4714 0.00855 0.00254 -0.1952 0.7040 0.0415
-3.500 0.4992 0.00844 0.00244 -0.1952 0.7011 0.0436
-3.250 0.5269 0.00834 0.00234 -0.1952 0.6981 0.0456
-3.000 0.5545 0.00828 0.00226 -0.1952 0.6952 0.0475
-2.750 0.5819 0.00821 0.00217 -0.1951 0.6926 0.0499
-2.500 0.6098 0.00814 0.00212 -0.1952 0.6903 0.0533
-2.250 0.6377 0.00807 0.00207 -0.1953 0.6876 0.0575
-2.000 0.6653 0.00800 0.00202 -0.1953 0.6846 0.0619
-1.750 0.6926 0.00795 0.00197 -0.1952 0.6811 0.0665
-1.500 0.7194 0.00791 0.00193 -0.1950 0.6774 0.0722
-1.250 0.7467 0.00787 0.00190 -0.1949 0.6739 0.0779
-1.000 0.7741 0.00782 0.00188 -0.1949 0.6703 0.0855
-0.750 0.8010 0.00778 0.00186 -0.1948 0.6665 0.0963
-0.500 0.8274 0.00775 0.00186 -0.1945 0.6624 0.1089
-0.250 0.8540 0.00773 0.00186 -0.1943 0.6583 0.1224
0.000 0.8805 0.00770 0.00187 -0.1941 0.6530 0.1376
0.250 0.9061 0.00770 0.00188 -0.1938 0.6476 0.1543
0.500 0.9319 0.00769 0.00191 -0.1934 0.6426 0.1738
0.750 0.9580 0.00766 0.00195 -0.1932 0.6378 0.2044
1.000 0.9829 0.00761 0.00200 -0.1927 0.6325 0.2506
1.250 1.0074 0.00758 0.00206 -0.1921 0.6269 0.2996
1.500 1.0323 0.00753 0.00213 -0.1917 0.6208 0.3577
1.750 1.0552 0.00749 0.00222 -0.1908 0.6143 0.4275
2.000 1.0777 0.00732 0.00234 -0.1900 0.6077 0.5640
2.250 1.0968 0.00723 0.00251 -0.1883 0.5983 0.6941
2.500 1.1183 0.00729 0.00265 -0.1870 0.5886 0.7449
2.750 1.1388 0.00743 0.00278 -0.1855 0.5793 0.7695
3.250 1.1789 0.00770 0.00305 -0.1824 0.5601 0.8077
3.500 1.1946 0.00785 0.00320 -0.1800 0.5503 0.8271
3.750 1.2117 0.00798 0.00335 -0.1778 0.5404 0.8487
4.000 1.2261 0.00816 0.00356 -0.1751 0.5292 0.8801
4.250 1.2447 0.00837 0.00380 -0.1734 0.5160 0.9180
4.500 1.2946 0.00871 0.00411 -0.1789 0.4996 0.9573
4.750 1.3176 0.00909 0.00441 -0.1784 0.4833 1.0000
5.000 1.3386 0.00944 0.00470 -0.1774 0.4700 1.0000
5.250 1.3599 0.00981 0.00501 -0.1766 0.4569 1.0000
5.500 1.3803 0.01025 0.00539 -0.1756 0.4427 1.0000
5.750 1.3998 0.01076 0.00582 -0.1746 0.4272 1.0000
6.000 1.4198 0.01127 0.00627 -0.1737 0.4141 1.0000
6.250 1.4387 0.01183 0.00678 -0.1728 0.4011 1.0000
6.500 1.4591 0.01232 0.00724 -0.1720 0.3908 1.0000
6.750 1.4782 0.01289 0.00777 -0.1711 0.3814 1.0000
7.000 1.4964 0.01350 0.00835 -0.1701 0.3717 1.0000
7.250 1.5148 0.01411 0.00895 -0.1692 0.3622 1.0000
7.500 1.5307 0.01487 0.00967 -0.1679 0.3514 1.0000
8.000 1.5590 0.01664 0.01134 -0.1651 0.3248 1.0000
8.250 1.5726 0.01757 0.01222 -0.1636 0.3121 1.0000
8.500 1.5858 0.01852 0.01314 -0.1622 0.3009 1.0000
8.750 1.5975 0.01958 0.01415 -0.1606 0.2882 1.0000
9.000 1.6119 0.02046 0.01502 -0.1593 0.2783 1.0000
9.250 1.6217 0.02165 0.01615 -0.1575 0.2645 1.0000
9.500 1.6315 0.02284 0.01728 -0.1557 0.2509 1.0000
9.750 1.6393 0.02416 0.01855 -0.1537 0.2363 1.0000
10.000 1.6473 0.02547 0.01980 -0.1518 0.2225 1.0000
10.250 1.6536 0.02693 0.02119 -0.1497 0.2076 1.0000
10.500 1.6586 0.02849 0.02266 -0.1475 0.1909 1.0000
10.750 1.6628 0.03015 0.02424 -0.1454 0.1749 1.0000
11.000 1.6712 0.03154 0.02560 -0.1437 0.1651 1.0000
11.250 1.6782 0.03307 0.02709 -0.1419 0.1554 1.0000
11.500 1.6886 0.03434 0.02837 -0.1405 0.1482 1.0000
11.750 1.6950 0.03595 0.02995 -0.1388 0.1391 1.0000
12.000 1.7034 0.03744 0.03142 -0.1374 0.1307 1.0000
12.250 1.7073 0.03932 0.03324 -0.1355 0.1183 1.0000
12.500 1.7137 0.04103 0.03493 -0.1340 0.1108 1.0000
12.750 1.7177 0.04293 0.03679 -0.1323 0.1009 1.0000
13.000 1.7233 0.04477 0.03862 -0.1308 0.0925 1.0000
13.250 1.7244 0.04701 0.04081 -0.1290 0.0803 1.0000
13.500 1.7206 0.04979 0.04351 -0.1270 0.0651 1.0000
13.750 1.7125 0.05300 0.04663 -0.1248 0.0483 1.0000
14.000 1.7126 0.05550 0.04911 -0.1232 0.0407 1.0000
14.250 1.7148 0.05789 0.05151 -0.1219 0.0363 1.0000
14.500 1.7168 0.06029 0.05392 -0.1207 0.0314 1.0000
14.750 1.7196 0.06266 0.05633 -0.1196 0.0282 1.0000
15.000 1.7225 0.06500 0.05870 -0.1185 0.0255 1.0000
15.250 1.7245 0.06752 0.06125 -0.1175 0.0235 1.0000
15.500 1.7274 0.06993 0.06370 -0.1166 0.0218 1.0000
15.750 1.7305 0.07239 0.06622 -0.1158 0.0208 1.0000
16.000 1.7332 0.07488 0.06875 -0.1150 0.0198 1.0000
16.250 1.7337 0.07766 0.07159 -0.1142 0.0187 1.0000
16.500 1.7365 0.08016 0.07415 -0.1135 0.0181 1.0000
16.750 1.7383 0.08282 0.07688 -0.1129 0.0173 1.0000
17.000 1.7391 0.08563 0.07974 -0.1124 0.0165 1.0000
17.250 1.7389 0.08857 0.08275 -0.1118 0.0157 1.0000
17.500 1.7383 0.09161 0.08585 -0.1114 0.0150 1.0000
17.750 1.7395 0.09440 0.08871 -0.1111 0.0142 1.0000
18.000 1.7378 0.09758 0.09195 -0.1108 0.0133 1.0000
18.250 1.7354 0.10085 0.09528 -0.1105 0.0125 1.0000
18.500 1.7343 0.10399 0.09848 -0.1104 0.0119 1.0000
18.750 1.7319 0.10734 0.10190 -0.1104 0.0111 1.0000
19.000 1.7294 0.11069 0.10531 -0.1104 0.0103 1.0000
19.250 1.7259 0.11423 0.10891 -0.1106 0.0098 1.0000
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Polar data table (+)
Polar graphs
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