FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-CL6-140 (fx74cl6140-il) Reynolds number: 500,000 Max Cl/Cd: 114.75 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74cl6140-il-500000.txt Download as CSV file: xf-fx74cl6140-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0644 0.09408 0.08976 -0.0757 0.5279 0.0146
-9.750 0.0640 0.09062 0.08631 -0.0779 0.5270 0.0151
-9.500 0.0638 0.08737 0.08308 -0.0798 0.5260 0.0152
-9.250 0.0785 0.08424 0.07996 -0.0793 0.5240 0.0154
-9.000 0.0866 0.08149 0.07720 -0.0799 0.5225 0.0156
-8.750 0.0940 0.07876 0.07448 -0.0806 0.5209 0.0158
-8.500 0.1010 0.07604 0.07176 -0.0814 0.5194 0.0162
-8.250 0.1075 0.07329 0.06900 -0.0822 0.5180 0.0171
-8.000 0.1126 0.07029 0.06601 -0.0832 0.5167 0.0175
-7.750 0.1117 0.06690 0.06263 -0.0853 0.5156 0.0181
-7.500 0.1099 0.06338 0.05913 -0.0877 0.5145 0.0183
-7.250 0.1153 0.06026 0.05600 -0.0882 0.5128 0.0184
-7.000 0.1259 0.05792 0.05366 -0.0878 0.5112 0.0186
-6.750 0.1335 0.05543 0.05119 -0.0881 0.5100 0.0188
-6.500 0.1389 0.05289 0.04868 -0.0887 0.5087 0.0191
-6.250 0.1427 0.05034 0.04616 -0.0892 0.5075 0.0194
-6.000 0.1435 0.04790 0.04375 -0.0895 0.5063 0.0198
-5.750 0.1488 0.04495 0.04083 -0.0916 0.5051 0.0201
-5.500 0.1565 0.04143 0.03731 -0.0955 0.5039 0.0208
-5.250 0.1744 0.03223 0.02795 -0.1129 0.5034 0.0217
-5.000 0.1870 0.03001 0.02574 -0.1129 0.5019 0.0220
-4.750 0.2044 0.02790 0.02359 -0.1142 0.5004 0.0224
-4.500 0.2257 0.02516 0.02076 -0.1170 0.4991 0.0230
-4.250 0.2603 0.01840 0.01355 -0.1253 0.4981 0.0258
-4.000 0.2825 0.01713 0.01225 -0.1262 0.4963 0.0263
-3.750 0.3090 0.01546 0.01044 -0.1280 0.4943 0.0278
-3.500 0.3426 0.01227 0.00688 -0.1315 0.4933 0.0308
-3.250 0.3765 0.01020 0.00437 -0.1340 0.4921 0.0352
-3.000 0.4031 0.00942 0.00363 -0.1349 0.4907 0.0364
-2.750 0.4346 0.00830 0.00222 -0.1364 0.4893 0.0417
-2.500 0.4875 0.01704 0.00977 -0.1440 0.4892 0.0246
-2.250 0.5180 0.01570 0.00821 -0.1443 0.4878 0.0235
-2.000 0.5477 0.01493 0.00729 -0.1445 0.4863 0.0237
-1.750 0.5771 0.01440 0.00665 -0.1447 0.4847 0.0241
-1.500 0.6064 0.01413 0.00628 -0.1448 0.4831 0.0253
-1.250 0.6358 0.01367 0.00579 -0.1452 0.4816 0.0262
-1.000 0.6654 0.01341 0.00552 -0.1456 0.4801 0.0271
-0.750 0.6951 0.01334 0.00539 -0.1460 0.4784 0.0288
-0.500 0.7249 0.01320 0.00525 -0.1464 0.4771 0.0314
-0.250 0.7544 0.01303 0.00510 -0.1467 0.4759 0.0367
0.000 0.7851 0.01261 0.00501 -0.1475 0.4745 0.1310
0.250 0.8170 0.01178 0.00508 -0.1492 0.4729 0.4850
0.500 0.8446 0.01167 0.00542 -0.1491 0.4714 0.6959
0.750 0.8719 0.01182 0.00558 -0.1487 0.4699 0.7380
1.000 0.8984 0.01192 0.00572 -0.1482 0.4685 0.7663
1.250 0.9255 0.01201 0.00579 -0.1479 0.4670 0.7847
1.500 0.9529 0.01209 0.00584 -0.1477 0.4655 0.7968
1.750 0.9801 0.01220 0.00592 -0.1475 0.4640 0.8104
2.000 1.0071 0.01237 0.00607 -0.1473 0.4626 0.8245
2.250 1.0346 0.01264 0.00632 -0.1473 0.4609 0.8342
2.500 1.0627 0.01268 0.00638 -0.1474 0.4597 0.8379
2.750 1.0905 0.01273 0.00645 -0.1475 0.4582 0.8414
3.000 1.1184 0.01281 0.00655 -0.1476 0.4566 0.8454
3.250 1.1465 0.01291 0.00666 -0.1478 0.4551 0.8494
3.500 1.1746 0.01301 0.00676 -0.1480 0.4534 0.8535
3.750 1.2022 0.01308 0.00684 -0.1481 0.4518 0.8583
4.000 1.2300 0.01315 0.00692 -0.1482 0.4502 0.8646
4.250 1.2576 0.01324 0.00701 -0.1483 0.4487 0.8717
4.500 1.2848 0.01337 0.00714 -0.1483 0.4473 0.8813
4.750 1.3111 0.01362 0.00742 -0.1482 0.4454 0.8974
5.000 1.3373 0.01362 0.00755 -0.1480 0.4440 1.0000
5.250 1.3654 0.01375 0.00771 -0.1483 0.4424 1.0000
5.500 1.3934 0.01390 0.00791 -0.1486 0.4406 1.0000
5.750 1.4212 0.01406 0.00809 -0.1489 0.4388 1.0000
6.000 1.4490 0.01419 0.00823 -0.1491 0.4370 1.0000
6.250 1.4768 0.01432 0.00836 -0.1494 0.4352 1.0000
6.500 1.5047 0.01445 0.00850 -0.1496 0.4335 1.0000
6.750 1.5324 0.01464 0.00867 -0.1499 0.4320 1.0000
7.000 1.5601 0.01496 0.00897 -0.1502 0.4301 1.0000
7.250 1.5861 0.01516 0.00926 -0.1502 0.4283 1.0000
7.500 1.6118 0.01531 0.00949 -0.1501 0.4263 1.0000
7.750 1.6377 0.01548 0.00973 -0.1500 0.4242 1.0000
8.000 1.6639 0.01563 0.00994 -0.1500 0.4222 1.0000
8.250 1.6902 0.01577 0.01011 -0.1500 0.4201 1.0000
8.500 1.7168 0.01589 0.01025 -0.1501 0.4181 1.0000
8.750 1.7434 0.01607 0.01045 -0.1502 0.4162 1.0000
9.000 1.7695 0.01640 0.01080 -0.1503 0.4139 1.0000
9.250 1.7929 0.01657 0.01111 -0.1498 0.4117 1.0000
9.500 1.8169 0.01673 0.01138 -0.1495 0.4090 1.0000
9.750 1.8413 0.01682 0.01152 -0.1492 0.4060 1.0000
10.000 1.8660 0.01675 0.01147 -0.1489 0.4023 1.0000
10.250 1.8884 0.01682 0.01160 -0.1483 0.3975 1.0000
10.500 1.9094 0.01683 0.01171 -0.1474 0.3920 1.0000
10.750 1.9312 0.01685 0.01175 -0.1466 0.3868 1.0000
11.000 1.9512 0.01703 0.01204 -0.1457 0.3812 1.0000
11.250 1.9703 0.01717 0.01224 -0.1445 0.3741 1.0000
11.500 1.9886 0.01743 0.01257 -0.1433 0.3677 1.0000
11.750 2.0066 0.01775 0.01297 -0.1421 0.3616 1.0000
12.000 2.0212 0.01815 0.01341 -0.1403 0.3559 1.0000
12.250 2.0337 0.01856 0.01393 -0.1382 0.3487 1.0000
12.500 2.0409 0.01915 0.01454 -0.1353 0.3416 1.0000
12.750 2.0485 0.01981 0.01529 -0.1327 0.3332 1.0000
13.000 2.0518 0.02072 0.01625 -0.1296 0.3250 1.0000
13.250 2.0501 0.02199 0.01754 -0.1264 0.3157 1.0000
13.500 2.0472 0.02354 0.01916 -0.1234 0.3052 1.0000
13.750 2.0388 0.02568 0.02134 -0.1205 0.2950 1.0000
14.000 2.0243 0.02867 0.02436 -0.1179 0.2847 1.0000
14.250 2.0057 0.03250 0.02824 -0.1160 0.2736 1.0000
14.500 1.9847 0.03703 0.03283 -0.1147 0.2626 1.0000
14.750 1.9584 0.04246 0.03831 -0.1137 0.2522 1.0000
15.000 1.9291 0.04842 0.04431 -0.1130 0.2433 1.0000
15.250 1.8991 0.05462 0.05055 -0.1125 0.2325 1.0000
15.500 1.8706 0.06087 0.05683 -0.1123 0.2214 1.0000
15.750 1.8430 0.06730 0.06327 -0.1125 0.2097 1.0000
16.000 1.8162 0.07389 0.06985 -0.1129 0.1971 1.0000
16.250 1.7911 0.08049 0.07643 -0.1136 0.1840 1.0000
16.500 1.7669 0.08718 0.08309 -0.1145 0.1701 1.0000
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