FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-CL6-140 (fx74cl6140-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.87 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74cl6140-il-1000000.txt Download as CSV file: xf-fx74cl6140-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-CL6-140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0630 0.09354 0.08984 -0.0779 0.4988 0.0096
-10.000 0.0683 0.09042 0.08671 -0.0790 0.4972 0.0097
-9.750 0.0702 0.08686 0.08314 -0.0806 0.4957 0.0097
-9.500 0.0747 0.08358 0.07986 -0.0817 0.4943 0.0098
-9.250 0.0827 0.08021 0.07651 -0.0820 0.4936 0.0100
-9.000 0.0900 0.07739 0.07370 -0.0828 0.4928 0.0100
-8.750 0.0971 0.07462 0.07093 -0.0835 0.4918 0.0101
-8.500 0.1047 0.07206 0.06839 -0.0842 0.4905 0.0103
-8.250 0.1120 0.06947 0.06581 -0.0850 0.4894 0.0107
-8.000 0.1175 0.06653 0.06287 -0.0858 0.4883 0.0108
-7.750 0.1231 0.06365 0.06000 -0.0867 0.4871 0.0110
-7.500 0.1283 0.06077 0.05714 -0.0875 0.4859 0.0114
-7.250 0.1327 0.05779 0.05416 -0.0884 0.4847 0.0116
-7.000 0.1347 0.05445 0.05083 -0.0896 0.4837 0.0121
-6.750 0.1313 0.05048 0.04689 -0.0917 0.4829 0.0123
-6.500 0.1305 0.04742 0.04385 -0.0924 0.4818 0.0123
-6.250 0.1306 0.04449 0.04094 -0.0936 0.4805 0.0124
-6.000 0.1360 0.04073 0.03718 -0.0971 0.4792 0.0124
-5.750 0.1417 0.03684 0.03329 -0.1011 0.4776 0.0126
-5.500 0.1551 0.03327 0.02970 -0.1062 0.4770 0.0127
-5.250 0.1713 0.03030 0.02671 -0.1097 0.4763 0.0128
-5.000 0.1901 0.02695 0.02331 -0.1138 0.4755 0.0131
-4.750 0.2119 0.02344 0.01973 -0.1180 0.4745 0.0134
-4.500 0.2370 0.01966 0.01581 -0.1224 0.4735 0.0139
-4.250 0.2726 0.01187 0.00752 -0.1305 0.4727 0.0156
-4.000 0.2990 0.01097 0.00655 -0.1317 0.4713 0.0160
-3.500 0.3824 0.01550 0.00943 -0.1443 0.4702 0.0154
-3.250 0.4121 0.01434 0.00812 -0.1448 0.4688 0.0149
-3.000 0.4420 0.01375 0.00730 -0.1451 0.4675 0.0152
-2.750 0.4716 0.01267 0.00607 -0.1455 0.4661 0.0151
-2.500 0.5011 0.01183 0.00510 -0.1458 0.4646 0.0154
-2.250 0.5301 0.01135 0.00458 -0.1461 0.4627 0.0160
-2.000 0.5591 0.01114 0.00432 -0.1463 0.4609 0.0165
-1.750 0.5887 0.01086 0.00402 -0.1466 0.4601 0.0169
-1.500 0.6182 0.01062 0.00377 -0.1469 0.4592 0.0174
-1.250 0.6477 0.01045 0.00358 -0.1472 0.4581 0.0180
-1.000 0.6774 0.01023 0.00334 -0.1475 0.4570 0.0189
-0.750 0.7069 0.01009 0.00320 -0.1478 0.4557 0.0199
-0.500 0.7363 0.01000 0.00308 -0.1481 0.4544 0.0214
-0.250 0.7657 0.00990 0.00297 -0.1484 0.4530 0.0240
0.000 0.7952 0.00978 0.00288 -0.1487 0.4517 0.0375
0.250 0.8250 0.00956 0.00289 -0.1492 0.4504 0.1219
0.500 0.8550 0.00930 0.00294 -0.1500 0.4490 0.2644
0.750 0.8855 0.00867 0.00316 -0.1512 0.4472 0.6495
1.000 0.9136 0.00885 0.00334 -0.1512 0.4451 0.6903
1.250 0.9420 0.00889 0.00342 -0.1512 0.4443 0.7141
1.500 0.9701 0.00897 0.00351 -0.1511 0.4435 0.7352
1.750 0.9984 0.00901 0.00357 -0.1512 0.4424 0.7452
2.000 1.0268 0.00908 0.00363 -0.1512 0.4411 0.7536
2.250 1.0547 0.00913 0.00369 -0.1512 0.4397 0.7646
2.500 1.0830 0.00920 0.00376 -0.1513 0.4384 0.7732
2.750 1.1111 0.00924 0.00381 -0.1514 0.4371 0.7779
3.000 1.1394 0.00930 0.00386 -0.1515 0.4357 0.7804
3.250 1.1676 0.00938 0.00392 -0.1517 0.4342 0.7827
3.500 1.1957 0.00949 0.00400 -0.1518 0.4326 0.7849
3.750 1.2236 0.00966 0.00414 -0.1519 0.4306 0.7872
4.000 1.2516 0.00979 0.00427 -0.1521 0.4291 0.7896
4.250 1.2796 0.00981 0.00433 -0.1522 0.4281 0.7926
4.500 1.3076 0.00986 0.00442 -0.1524 0.4268 0.7957
4.750 1.3356 0.00993 0.00451 -0.1525 0.4255 0.7988
5.000 1.3635 0.01000 0.00460 -0.1527 0.4240 0.8020
5.250 1.3913 0.01007 0.00468 -0.1529 0.4224 0.8054
5.500 1.4188 0.01013 0.00478 -0.1530 0.4208 0.8094
5.750 1.4463 0.01021 0.00488 -0.1531 0.4192 0.8140
6.000 1.4735 0.01033 0.00501 -0.1531 0.4175 0.8195
6.250 1.5003 0.01051 0.00521 -0.1532 0.4153 0.8262
6.500 1.5273 0.01061 0.00537 -0.1532 0.4137 0.8348
6.750 1.5543 0.01064 0.00548 -0.1533 0.4123 0.8471
7.000 1.5803 0.01065 0.00562 -0.1531 0.4107 0.8735
7.250 1.6051 0.01058 0.00571 -0.1527 0.4090 1.0000
7.500 1.6324 0.01068 0.00584 -0.1528 0.4071 1.0000
7.750 1.6594 0.01079 0.00598 -0.1530 0.4051 1.0000
8.000 1.6860 0.01094 0.00613 -0.1530 0.4030 1.0000
8.250 1.7119 0.01117 0.00635 -0.1530 0.4004 1.0000
8.500 1.7384 0.01130 0.00654 -0.1530 0.3985 1.0000
8.750 1.7650 0.01140 0.00670 -0.1531 0.3964 1.0000
9.000 1.7913 0.01149 0.00685 -0.1531 0.3935 1.0000
9.250 1.8169 0.01158 0.00695 -0.1530 0.3891 1.0000
9.500 1.8415 0.01176 0.00713 -0.1528 0.3840 1.0000
9.750 1.8676 0.01183 0.00727 -0.1528 0.3789 1.0000
10.000 1.8915 0.01203 0.00746 -0.1525 0.3725 1.0000
10.250 1.9163 0.01220 0.00767 -0.1523 0.3661 1.0000
10.500 1.9390 0.01247 0.00794 -0.1518 0.3582 1.0000
10.750 1.9625 0.01271 0.00822 -0.1515 0.3506 1.0000
11.000 1.9835 0.01308 0.00857 -0.1507 0.3432 1.0000
11.250 2.0057 0.01337 0.00892 -0.1502 0.3353 1.0000
11.500 2.0248 0.01382 0.00936 -0.1492 0.3262 1.0000
11.750 2.0422 0.01433 0.00986 -0.1479 0.3158 1.0000
12.000 2.0582 0.01488 0.01041 -0.1464 0.3044 1.0000
12.250 2.0685 0.01559 0.01110 -0.1440 0.2909 1.0000
12.500 2.0708 0.01647 0.01194 -0.1402 0.2759 1.0000
12.750 2.0658 0.01770 0.01310 -0.1356 0.2592 1.0000
13.000 2.0577 0.01918 0.01454 -0.1310 0.2431 1.0000
13.250 2.0417 0.02133 0.01664 -0.1262 0.2255 1.0000
13.500 2.0207 0.02428 0.01957 -0.1221 0.2098 1.0000
13.750 1.9942 0.02842 0.02373 -0.1189 0.1955 1.0000
14.000 1.9695 0.03324 0.02859 -0.1172 0.1852 1.0000
14.250 1.9398 0.03909 0.03449 -0.1161 0.1758 1.0000
14.500 1.9123 0.04493 0.04039 -0.1153 0.1674 1.0000
14.750 1.8832 0.05100 0.04653 -0.1146 0.1603 1.0000
15.000 1.8532 0.05732 0.05289 -0.1142 0.1520 1.0000
15.250 1.8255 0.06365 0.05924 -0.1141 0.1419 1.0000
15.500 1.8020 0.06972 0.06533 -0.1143 0.1321 1.0000
15.750 1.7795 0.07591 0.07152 -0.1148 0.1212 1.0000
16.000 1.7574 0.08225 0.07784 -0.1155 0.1088 1.0000
16.250 1.7371 0.08851 0.08406 -0.1164 0.0960 1.0000
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