FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 500,000 Max Cl/Cd: 107.75 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-500000-n5.txt Download as CSV file: xf-fx73cl2152-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4651 0.05320 0.04993 -0.1085 0.9673 0.0262
-11.250 -0.4963 0.04538 0.04195 -0.1152 0.9553 0.0264
-11.000 -0.5130 0.03854 0.03495 -0.1223 0.9443 0.0265
-10.750 -0.5021 0.03203 0.02823 -0.1332 0.9359 0.0269
-10.500 -0.4717 0.02671 0.02265 -0.1453 0.9277 0.0273
-10.250 -0.4412 0.02398 0.01969 -0.1515 0.9185 0.0277
-9.750 -0.3696 0.02062 0.01600 -0.1598 0.9000 0.0285
-9.500 -0.3214 0.01928 0.01456 -0.1652 0.8871 0.0290
-9.250 -0.2367 0.01781 0.01289 -0.1776 0.8603 0.0298
-9.000 -0.1487 0.01705 0.01158 -0.1907 0.7775 0.0309
-8.750 -0.1224 0.01686 0.01096 -0.1911 0.7094 0.0315
-8.500 -0.0991 0.01658 0.01037 -0.1907 0.6615 0.0319
-8.250 -0.0736 0.01628 0.00980 -0.1907 0.6257 0.0324
-8.000 -0.0460 0.01586 0.00923 -0.1913 0.5976 0.0329
-7.750 -0.0176 0.01555 0.00878 -0.1918 0.5758 0.0334
-7.500 0.0115 0.01527 0.00836 -0.1923 0.5580 0.0340
-7.250 0.0409 0.01499 0.00797 -0.1929 0.5429 0.0347
-7.000 0.0705 0.01474 0.00759 -0.1934 0.5297 0.0355
-6.750 0.1004 0.01450 0.00722 -0.1939 0.5177 0.0364
-6.500 0.1308 0.01423 0.00685 -0.1946 0.5078 0.0371
-6.250 0.1614 0.01396 0.00651 -0.1953 0.4981 0.0380
-6.000 0.1916 0.01376 0.00623 -0.1958 0.4900 0.0388
-5.750 0.2220 0.01357 0.00596 -0.1964 0.4819 0.0398
-5.250 0.2826 0.01325 0.00547 -0.1973 0.4685 0.0419
-5.000 0.3137 0.01304 0.00524 -0.1980 0.4629 0.0433
-4.750 0.3439 0.01293 0.00505 -0.1984 0.4577 0.0447
-4.500 0.3741 0.01282 0.00488 -0.1988 0.4533 0.0462
-4.250 0.4049 0.01268 0.00470 -0.1993 0.4495 0.0477
-4.000 0.4356 0.01255 0.00454 -0.1998 0.4455 0.0496
-3.750 0.4657 0.01248 0.00442 -0.2001 0.4416 0.0520
-3.500 0.4959 0.01241 0.00430 -0.2005 0.4376 0.0546
-3.250 0.5261 0.01234 0.00420 -0.2008 0.4341 0.0579
-2.750 0.5869 0.01220 0.00403 -0.2016 0.4282 0.0668
-2.500 0.6173 0.01213 0.00396 -0.2020 0.4253 0.0752
-2.250 0.6481 0.01205 0.00391 -0.2025 0.4226 0.0903
-2.000 0.6787 0.01199 0.00390 -0.2030 0.4196 0.1149
-1.500 0.7386 0.01196 0.00395 -0.2037 0.4144 0.1586
-1.250 0.7681 0.01196 0.00398 -0.2038 0.4122 0.1738
-1.000 0.7974 0.01199 0.00402 -0.2040 0.4097 0.1868
-0.750 0.8263 0.01203 0.00406 -0.2040 0.4069 0.1984
-0.500 0.8552 0.01208 0.00411 -0.2040 0.4039 0.2108
-0.250 0.8839 0.01215 0.00418 -0.2040 0.4013 0.2238
0.000 0.9125 0.01223 0.00427 -0.2041 0.3987 0.2423
0.250 0.9415 0.01229 0.00436 -0.2041 0.3967 0.2594
0.500 0.9705 0.01233 0.00443 -0.2042 0.3947 0.2726
0.750 0.9992 0.01238 0.00451 -0.2042 0.3924 0.2843
1.000 1.0277 0.01245 0.00460 -0.2042 0.3901 0.2985
1.250 1.0561 0.01252 0.00470 -0.2041 0.3876 0.3152
1.500 1.0843 0.01261 0.00481 -0.2041 0.3852 0.3321
1.750 1.1123 0.01272 0.00493 -0.2040 0.3828 0.3512
2.000 1.1401 0.01285 0.00508 -0.2038 0.3806 0.3721
2.250 1.1682 0.01295 0.00522 -0.2038 0.3788 0.3921
2.500 1.1965 0.01302 0.00536 -0.2037 0.3771 0.4130
2.750 1.2247 0.01311 0.00551 -0.2037 0.3752 0.4364
3.000 1.2525 0.01321 0.00566 -0.2035 0.3731 0.4594
3.250 1.2801 0.01331 0.00582 -0.2034 0.3707 0.4817
3.500 1.3073 0.01343 0.00599 -0.2031 0.3683 0.5071
3.750 1.3340 0.01357 0.00617 -0.2028 0.3658 0.5331
4.000 1.3602 0.01373 0.00636 -0.2024 0.3633 0.5565
4.250 1.3869 0.01388 0.00656 -0.2021 0.3613 0.5809
4.500 1.4139 0.01398 0.00676 -0.2018 0.3594 0.6072
4.750 1.4404 0.01410 0.00695 -0.2014 0.3572 0.6344
5.000 1.4664 0.01423 0.00716 -0.2010 0.3548 0.6608
5.250 1.4919 0.01437 0.00737 -0.2004 0.3524 0.6891
5.500 1.5168 0.01452 0.00759 -0.1998 0.3499 0.7188
6.000 1.5644 0.01487 0.00807 -0.1980 0.3447 0.7906
6.250 1.5861 0.01490 0.00828 -0.1966 0.3424 0.8554
6.500 1.5992 0.01486 0.00836 -0.1935 0.3400 1.0000
6.750 1.6238 0.01507 0.00859 -0.1928 0.3373 1.0000
7.000 1.6478 0.01530 0.00882 -0.1920 0.3345 1.0000
7.250 1.6708 0.01556 0.00907 -0.1911 0.3318 1.0000
7.500 1.6931 0.01585 0.00935 -0.1901 0.3291 1.0000
7.750 1.7167 0.01608 0.00963 -0.1893 0.3266 1.0000
8.000 1.7400 0.01632 0.00990 -0.1885 0.3235 1.0000
8.250 1.7625 0.01658 0.01019 -0.1875 0.3202 1.0000
8.500 1.7842 0.01688 0.01051 -0.1864 0.3170 1.0000
8.750 1.8044 0.01723 0.01085 -0.1851 0.3135 1.0000
9.000 1.8258 0.01752 0.01118 -0.1839 0.3087 1.0000
9.250 1.8451 0.01788 0.01153 -0.1825 0.3016 1.0000
9.500 1.8629 0.01832 0.01195 -0.1808 0.2949 1.0000
9.750 1.8825 0.01870 0.01236 -0.1795 0.2887 1.0000
10.000 1.8993 0.01921 0.01286 -0.1777 0.2830 1.0000
10.250 1.9172 0.01968 0.01336 -0.1761 0.2779 1.0000
10.500 1.9348 0.02018 0.01388 -0.1745 0.2723 1.0000
10.750 1.9496 0.02081 0.01451 -0.1726 0.2672 1.0000
11.000 1.9661 0.02137 0.01511 -0.1709 0.2630 1.0000
11.250 1.9824 0.02195 0.01574 -0.1692 0.2584 1.0000
11.500 1.9960 0.02267 0.01648 -0.1672 0.2536 1.0000
11.750 2.0087 0.02345 0.01729 -0.1651 0.2493 1.0000
12.000 2.0233 0.02415 0.01805 -0.1633 0.2444 1.0000
12.250 2.0346 0.02505 0.01898 -0.1612 0.2390 1.0000
12.500 2.0440 0.02608 0.02003 -0.1589 0.2340 1.0000
12.750 2.0556 0.02700 0.02102 -0.1570 0.2287 1.0000
13.000 2.0628 0.02823 0.02229 -0.1546 0.2228 1.0000
13.250 2.0702 0.02950 0.02360 -0.1524 0.2171 1.0000
13.500 2.0752 0.03099 0.02513 -0.1502 0.2096 1.0000
13.750 2.0766 0.03282 0.02699 -0.1477 0.2016 1.0000
14.000 2.0724 0.03520 0.02939 -0.1451 0.1916 1.0000
14.250 2.0668 0.03790 0.03210 -0.1428 0.1806 1.0000
14.500 2.0558 0.04133 0.03557 -0.1407 0.1698 1.0000
14.750 2.0396 0.04564 0.03990 -0.1390 0.1593 1.0000
15.000 2.0203 0.05074 0.04505 -0.1379 0.1502 1.0000
15.250 1.9998 0.05642 0.05082 -0.1376 0.1419 1.0000
15.500 1.9772 0.06277 0.05726 -0.1378 0.1354 1.0000
15.750 1.9537 0.06954 0.06413 -0.1385 0.1294 1.0000
16.000 1.9284 0.07683 0.07152 -0.1396 0.1244 1.0000
16.250 1.9066 0.08377 0.07857 -0.1409 0.1193 1.0000
16.500 1.8822 0.09127 0.08616 -0.1425 0.1147 1.0000
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