FX 76-MP-140 (fx76mp140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 76-MP-140 (fx76mp140-il) Reynolds number: 200,000 Max Cl/Cd: 78.27 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76mp140-il-200000-n5.txt Download as CSV file: xf-fx76mp140-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.1124 0.10599 0.10094 -0.1467 0.8367 0.0250
-11.750 0.1167 0.10265 0.09760 -0.1483 0.8342 0.0261
-11.500 0.1150 0.09837 0.09332 -0.1507 0.8317 0.0267
-11.000 0.1349 0.09351 0.08844 -0.1529 0.8276 0.0271
-10.750 0.1458 0.09128 0.08618 -0.1541 0.8258 0.0277
-10.500 0.1544 0.08887 0.08377 -0.1554 0.8239 0.0290
-10.250 0.1577 0.08587 0.08080 -0.1564 0.8215 0.0285
-10.000 0.1613 0.08312 0.07807 -0.1574 0.8187 0.0297
-9.750 0.1588 0.07936 0.07432 -0.1591 0.8160 0.0305
-9.500 0.1602 0.07605 0.07102 -0.1604 0.8134 0.0306
-9.250 0.1628 0.07307 0.06806 -0.1615 0.8111 0.0315
-9.000 0.1720 0.07124 0.06620 -0.1622 0.8092 0.0320
-8.750 0.1801 0.06921 0.06416 -0.1631 0.8073 0.0331
-8.500 0.1773 0.06620 0.06121 -0.1635 0.8045 0.0331
-8.250 0.1720 0.06300 0.05807 -0.1640 0.8012 0.0333
-8.000 0.1643 0.05963 0.05475 -0.1644 0.7978 0.0336
-7.750 0.1484 0.05590 0.05107 -0.1648 0.7945 0.0334
-7.500 0.0578 0.03135 0.02568 -0.1848 0.7884 0.0344
-7.250 0.0624 0.02641 0.01986 -0.1862 0.7849 0.0359
-7.000 0.0835 0.02539 0.01872 -0.1861 0.7823 0.0366
-6.750 0.1067 0.02459 0.01781 -0.1861 0.7801 0.0374
-6.500 0.1309 0.02361 0.01663 -0.1863 0.7781 0.0383
-6.250 0.1566 0.02254 0.01530 -0.1867 0.7762 0.0396
-6.000 0.1835 0.02147 0.01388 -0.1871 0.7746 0.0414
-5.750 0.2113 0.02090 0.01323 -0.1876 0.7731 0.0429
-5.500 0.2331 0.02059 0.01291 -0.1869 0.7704 0.0443
-5.250 0.2560 0.02013 0.01234 -0.1863 0.7675 0.0460
-5.000 0.2808 0.01958 0.01161 -0.1860 0.7649 0.0479
-4.750 0.3066 0.01916 0.01117 -0.1859 0.7626 0.0497
-4.500 0.3337 0.01888 0.01084 -0.1860 0.7607 0.0522
-4.250 0.3621 0.01849 0.01032 -0.1862 0.7589 0.0551
-4.000 0.3912 0.01809 0.00987 -0.1866 0.7572 0.0577
-3.750 0.4176 0.01789 0.00965 -0.1865 0.7550 0.0608
-3.500 0.4382 0.01780 0.00953 -0.1853 0.7512 0.0639
-3.250 0.4625 0.01757 0.00931 -0.1849 0.7482 0.0672
-3.000 0.4889 0.01738 0.00910 -0.1847 0.7456 0.0712
-2.750 0.5168 0.01714 0.00880 -0.1848 0.7435 0.0751
-2.500 0.5459 0.01685 0.00852 -0.1852 0.7417 0.0802
-2.250 0.5762 0.01662 0.00822 -0.1857 0.7400 0.0859
-2.000 0.5963 0.01660 0.00829 -0.1845 0.7362 0.0916
-1.750 0.6185 0.01659 0.00828 -0.1835 0.7325 0.0992
-1.500 0.6445 0.01643 0.00816 -0.1833 0.7295 0.1082
-1.250 0.6728 0.01624 0.00797 -0.1834 0.7270 0.1200
-1.000 0.7029 0.01602 0.00778 -0.1839 0.7250 0.1374
-0.750 0.7310 0.01587 0.00767 -0.1841 0.7226 0.1595
-0.500 0.7476 0.01600 0.00792 -0.1822 0.7176 0.1823
-0.250 0.7717 0.01591 0.00794 -0.1816 0.7141 0.2171
0.000 0.7992 0.01569 0.00786 -0.1817 0.7114 0.2685
0.250 0.8289 0.01537 0.00774 -0.1822 0.7091 0.3492
0.500 0.8523 0.01505 0.00783 -0.1816 0.7058 0.4853
0.750 0.8631 0.01492 0.00826 -0.1782 0.7004 0.6654
1.000 0.8831 0.01480 0.00833 -0.1762 0.6966 0.7740
1.250 0.9086 0.01465 0.00821 -0.1754 0.6938 0.8262
1.500 0.9325 0.01456 0.00813 -0.1744 0.6906 0.8631
1.750 0.9460 0.01473 0.00838 -0.1716 0.6846 0.8990
2.000 0.9796 0.01456 0.00823 -0.1728 0.6807 1.0000
2.250 1.0111 0.01448 0.00806 -0.1735 0.6774 1.0000
2.500 1.0298 0.01469 0.00825 -0.1720 0.6714 1.0000
2.750 1.0521 0.01480 0.00833 -0.1711 0.6658 1.0000
3.000 1.0828 0.01473 0.00819 -0.1716 0.6619 1.0000
3.250 1.1008 0.01496 0.00841 -0.1700 0.6558 1.0000
3.500 1.1206 0.01511 0.00854 -0.1686 0.6500 1.0000
3.750 1.1521 0.01504 0.00841 -0.1693 0.6458 1.0000
4.000 1.1637 0.01537 0.00876 -0.1665 0.6382 1.0000
4.250 1.1879 0.01545 0.00880 -0.1659 0.6323 1.0000
4.500 1.2096 0.01560 0.00892 -0.1649 0.6258 1.0000
4.750 1.2272 0.01583 0.00915 -0.1631 0.6177 1.0000
5.000 1.2500 0.01597 0.00925 -0.1623 0.6107 1.0000
5.250 1.2664 0.01627 0.00954 -0.1605 0.6018 1.0000
5.500 1.2874 0.01649 0.00974 -0.1595 0.5943 1.0000
5.750 1.3057 0.01678 0.01002 -0.1580 0.5853 1.0000
6.000 1.3244 0.01710 0.01033 -0.1567 0.5769 1.0000
6.250 1.3447 0.01737 0.01055 -0.1556 0.5674 1.0000
6.500 1.3592 0.01786 0.01104 -0.1537 0.5568 1.0000
6.750 1.3776 0.01823 0.01137 -0.1524 0.5464 1.0000
7.000 1.3938 0.01871 0.01180 -0.1508 0.5350 1.0000
7.250 1.4070 0.01932 0.01239 -0.1489 0.5225 1.0000
7.500 1.4203 0.01997 0.01300 -0.1470 0.5094 1.0000
7.750 1.4351 0.02059 0.01358 -0.1453 0.4981 1.0000
8.000 1.4484 0.02131 0.01427 -0.1436 0.4866 1.0000
8.250 1.4610 0.02210 0.01507 -0.1418 0.4755 1.0000
8.500 1.4731 0.02292 0.01586 -0.1401 0.4638 1.0000
8.750 1.4846 0.02380 0.01669 -0.1382 0.4517 1.0000
9.000 1.4948 0.02478 0.01768 -0.1363 0.4395 1.0000
9.250 1.5059 0.02574 0.01864 -0.1346 0.4285 1.0000
9.500 1.5164 0.02675 0.01963 -0.1328 0.4177 1.0000
9.750 1.5274 0.02778 0.02069 -0.1312 0.4072 1.0000
10.000 1.5378 0.02884 0.02177 -0.1295 0.3972 1.0000
10.250 1.5475 0.02995 0.02288 -0.1278 0.3870 1.0000
10.500 1.5573 0.03111 0.02408 -0.1262 0.3768 1.0000
10.750 1.5664 0.03232 0.02529 -0.1245 0.3669 1.0000
11.000 1.5744 0.03364 0.02662 -0.1228 0.3562 1.0000
11.250 1.5823 0.03500 0.02801 -0.1212 0.3451 1.0000
11.500 1.5886 0.03650 0.02952 -0.1194 0.3338 1.0000
11.750 1.5943 0.03808 0.03109 -0.1177 0.3226 1.0000
12.000 1.6001 0.03971 0.03275 -0.1161 0.3104 1.0000
12.250 1.6048 0.04146 0.03451 -0.1145 0.2983 1.0000
12.500 1.6082 0.04337 0.03642 -0.1128 0.2860 1.0000
12.750 1.6095 0.04552 0.03854 -0.1111 0.2717 1.0000
13.000 1.6105 0.04774 0.04075 -0.1095 0.2584 1.0000
13.250 1.6128 0.04991 0.04293 -0.1080 0.2454 1.0000
13.500 1.6148 0.05217 0.04519 -0.1067 0.2333 1.0000
13.750 1.6155 0.05460 0.04762 -0.1053 0.2211 1.0000
14.000 1.6157 0.05712 0.05013 -0.1040 0.2107 1.0000
14.250 1.6167 0.05963 0.05267 -0.1029 0.1998 1.0000
14.500 1.6187 0.06206 0.05514 -0.1019 0.1904 1.0000
14.750 1.6177 0.06487 0.05796 -0.1008 0.1813 1.0000
15.000 1.6197 0.06741 0.06054 -0.1000 0.1725 1.0000
15.250 1.6193 0.07025 0.06341 -0.0992 0.1643 1.0000
15.500 1.6173 0.07332 0.06650 -0.0984 0.1554 1.0000
15.750 1.6173 0.07620 0.06944 -0.0978 0.1466 1.0000
16.000 1.6145 0.07949 0.07275 -0.0972 0.1387 1.0000
16.250 1.6128 0.08270 0.07602 -0.0968 0.1289 1.0000
16.500 1.6109 0.08598 0.07934 -0.0965 0.1202 1.0000
16.750 1.6061 0.08967 0.08305 -0.0963 0.1110 1.0000
17.000 1.6006 0.09352 0.08692 -0.0963 0.1014 1.0000
17.250 1.5966 0.09722 0.09067 -0.0963 0.0908 1.0000
17.750 1.5794 0.10607 0.09951 -0.0971 0.0676 1.0000
18.000 1.5695 0.11077 0.10420 -0.0977 0.0572 1.0000
18.250 1.5597 0.11552 0.10895 -0.0985 0.0497 1.0000
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Polar data table (+)
Polar graphs
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