FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 500,000 Max Cl/Cd: 104.15 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-500000.txt Download as CSV file: xf-fx73cl2152-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL2-152
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0753 0.09894 0.09655 -0.0761 0.9731 0.0423
-9.250 -0.0553 0.09637 0.09399 -0.0781 0.9679 0.0427
-9.000 -0.2880 0.02845 0.02463 -0.1540 0.9414 0.0367
-8.750 -0.2586 0.02494 0.02086 -0.1591 0.9344 0.0374
-8.500 -0.2232 0.02335 0.01919 -0.1621 0.9286 0.0379
-8.250 -0.1935 0.02213 0.01791 -0.1634 0.9193 0.0385
-7.500 -0.0588 0.01780 0.01293 -0.1762 0.8761 0.0414
-7.250 0.0483 0.01569 0.01040 -0.1933 0.8176 0.0432
-7.000 0.0933 0.01559 0.00975 -0.1970 0.7272 0.0443
-6.750 0.1153 0.01548 0.00928 -0.1960 0.6710 0.0451
-6.250 0.1665 0.01509 0.00835 -0.1953 0.6021 0.0469
-6.000 0.1945 0.01455 0.00766 -0.1957 0.5783 0.0482
-5.750 0.2228 0.01431 0.00732 -0.1959 0.5591 0.0493
-5.500 0.2519 0.01409 0.00698 -0.1962 0.5437 0.0506
-5.250 0.2813 0.01390 0.00664 -0.1965 0.5310 0.0519
-5.000 0.3112 0.01373 0.00636 -0.1969 0.5206 0.0531
-4.750 0.3429 0.01332 0.00589 -0.1979 0.5115 0.0550
-4.500 0.3736 0.01313 0.00568 -0.1984 0.5040 0.0571
-4.250 0.4039 0.01303 0.00546 -0.1988 0.4969 0.0592
-4.000 0.4363 0.01276 0.00515 -0.1998 0.4908 0.0616
-3.750 0.4677 0.01259 0.00496 -0.2005 0.4853 0.0645
-3.500 0.4987 0.01248 0.00478 -0.2010 0.4798 0.0680
-3.250 0.5304 0.01239 0.00463 -0.2018 0.4744 0.0730
-3.000 0.5626 0.01222 0.00446 -0.2026 0.4707 0.0795
-2.750 0.5947 0.01206 0.00433 -0.2035 0.4669 0.0908
-2.500 0.6276 0.01187 0.00425 -0.2045 0.4631 0.1236
-2.250 0.6585 0.01184 0.00427 -0.2051 0.4593 0.1620
-2.000 0.6885 0.01195 0.00435 -0.2054 0.4551 0.1820
-1.750 0.7181 0.01198 0.00440 -0.2056 0.4522 0.1976
-1.500 0.7479 0.01199 0.00444 -0.2058 0.4495 0.2119
-1.250 0.7773 0.01203 0.00449 -0.2059 0.4464 0.2244
-1.000 0.8061 0.01211 0.00453 -0.2059 0.4432 0.2361
-0.750 0.8357 0.01217 0.00459 -0.2061 0.4399 0.2492
-0.500 0.8656 0.01234 0.00471 -0.2064 0.4363 0.2618
0.000 0.9243 0.01245 0.00489 -0.2066 0.4317 0.2958
0.250 0.9536 0.01249 0.00498 -0.2068 0.4290 0.3153
0.500 0.9829 0.01253 0.00507 -0.2069 0.4263 0.3339
0.750 1.0121 0.01260 0.00516 -0.2071 0.4237 0.3540
1.000 1.0412 0.01271 0.00528 -0.2072 0.4211 0.3770
1.250 1.0712 0.01290 0.00547 -0.2075 0.4179 0.4022
1.500 1.1010 0.01303 0.00566 -0.2078 0.4154 0.4281
1.750 1.1296 0.01309 0.00579 -0.2078 0.4136 0.4556
2.000 1.1582 0.01316 0.00594 -0.2078 0.4114 0.4836
2.250 1.1867 0.01325 0.00610 -0.2078 0.4091 0.5115
2.750 1.2431 0.01347 0.00642 -0.2077 0.4044 0.5682
3.000 1.2712 0.01363 0.00661 -0.2076 0.4020 0.5959
3.250 1.3004 0.01390 0.00687 -0.2078 0.3989 0.6224
3.500 1.3284 0.01405 0.00710 -0.2077 0.3966 0.6508
3.750 1.3550 0.01413 0.00727 -0.2073 0.3946 0.6788
4.000 1.3818 0.01422 0.00746 -0.2069 0.3923 0.7072
4.250 1.4083 0.01433 0.00765 -0.2065 0.3898 0.7382
4.500 1.4342 0.01444 0.00783 -0.2060 0.3875 0.7726
4.750 1.4589 0.01454 0.00801 -0.2052 0.3851 0.8128
5.000 1.4803 0.01464 0.00820 -0.2037 0.3827 0.8728
5.250 1.4984 0.01480 0.00839 -0.2015 0.3797 1.0000
5.500 1.5238 0.01492 0.00855 -0.2010 0.3779 1.0000
5.750 1.5492 0.01506 0.00872 -0.2004 0.3754 1.0000
6.000 1.5746 0.01522 0.00890 -0.1999 0.3726 1.0000
6.250 1.5998 0.01540 0.00908 -0.1993 0.3699 1.0000
6.500 1.6248 0.01560 0.00927 -0.1987 0.3674 1.0000
6.750 1.6503 0.01588 0.00952 -0.1983 0.3647 1.0000
7.000 1.6772 0.01625 0.00986 -0.1982 0.3616 1.0000
7.250 1.7002 0.01641 0.01009 -0.1972 0.3594 1.0000
7.500 1.7226 0.01659 0.01032 -0.1961 0.3567 1.0000
7.750 1.7445 0.01677 0.01053 -0.1949 0.3537 1.0000
8.000 1.7660 0.01697 0.01075 -0.1937 0.3508 1.0000
8.250 1.7883 0.01725 0.01101 -0.1927 0.3480 1.0000
8.500 1.8128 0.01766 0.01139 -0.1921 0.3447 1.0000
8.750 1.8313 0.01781 0.01164 -0.1903 0.3417 1.0000
9.000 1.8489 0.01796 0.01185 -0.1884 0.3373 1.0000
9.250 1.8658 0.01816 0.01205 -0.1863 0.3325 1.0000
9.500 1.8841 0.01853 0.01239 -0.1847 0.3278 1.0000
9.750 1.9032 0.01876 0.01272 -0.1831 0.3239 1.0000
10.000 1.9217 0.01905 0.01306 -0.1815 0.3196 1.0000
10.250 1.9388 0.01943 0.01343 -0.1797 0.3154 1.0000
10.500 1.9562 0.01990 0.01391 -0.1780 0.3115 1.0000
10.750 1.9751 0.02024 0.01434 -0.1766 0.3077 1.0000
11.000 1.9925 0.02066 0.01482 -0.1749 0.3035 1.0000
11.250 2.0080 0.02119 0.01535 -0.1730 0.2995 1.0000
11.500 2.0228 0.02179 0.01597 -0.1711 0.2957 1.0000
11.750 2.0404 0.02225 0.01653 -0.1696 0.2917 1.0000
12.000 2.0550 0.02284 0.01717 -0.1676 0.2872 1.0000
12.250 2.0669 0.02359 0.01793 -0.1654 0.2829 1.0000
12.500 2.0805 0.02430 0.01871 -0.1635 0.2789 1.0000
12.750 2.0948 0.02498 0.01947 -0.1617 0.2745 1.0000
13.000 2.1052 0.02588 0.02040 -0.1595 0.2699 1.0000
13.250 2.1125 0.02700 0.02154 -0.1570 0.2653 1.0000
13.500 2.1255 0.02782 0.02247 -0.1553 0.2606 1.0000
13.750 2.1329 0.02900 0.02369 -0.1530 0.2552 1.0000
14.000 2.1358 0.03054 0.02525 -0.1504 0.2500 1.0000
14.250 2.1456 0.03168 0.02650 -0.1487 0.2447 1.0000
14.500 2.1483 0.03337 0.02824 -0.1464 0.2387 1.0000
14.750 2.1496 0.03528 0.03021 -0.1443 0.2329 1.0000
15.000 2.1511 0.03728 0.03229 -0.1424 0.2257 1.0000
15.250 2.1459 0.04001 0.03506 -0.1404 0.2187 1.0000
15.500 2.1409 0.04294 0.03805 -0.1388 0.2095 1.0000
15.750 2.1309 0.04660 0.04177 -0.1374 0.2004 1.0000
16.000 2.1119 0.05159 0.04680 -0.1364 0.1903 1.0000
16.250 2.0885 0.05757 0.05283 -0.1360 0.1792 1.0000
16.500 2.0605 0.06456 0.05989 -0.1363 0.1684 1.0000
16.750 2.0260 0.07285 0.06826 -0.1373 0.1589 1.0000
17.000 1.9875 0.08211 0.07758 -0.1390 0.1503 1.0000
17.250 1.9545 0.09077 0.08631 -0.1409 0.1417 1.0000
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