FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 500,000 Max Cl/Cd: 99.08 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-500000.txt Download as CSV file: xf-fx73cl3152-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL3-152
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
------ -------- --------- --------- -------- -------- --------
-10.250 0.1961 0.09443 0.09149 -0.1272 0.8896 0.0349
-10.000 0.2050 0.09216 0.08920 -0.1281 0.8814 0.0359
-9.750 0.1892 0.08787 0.08489 -0.1328 0.8735 0.0374
-9.500 0.2068 0.08560 0.08258 -0.1324 0.8663 0.0377
-9.250 0.2194 0.08386 0.08084 -0.1317 0.8568 0.0379
-9.000 0.2329 0.08218 0.07912 -0.1317 0.8477 0.0383
-8.750 0.2416 0.08044 0.07737 -0.1315 0.8370 0.0387
-8.500 0.2501 0.07863 0.07552 -0.1315 0.8252 0.0397
-8.250 0.2310 0.07430 0.07117 -0.1353 0.8138 0.0421
-8.000 0.2383 0.07197 0.06882 -0.1345 0.7968 0.0424
-7.750 0.2478 0.07056 0.06732 -0.1333 0.7696 0.0426
-7.500 0.2535 0.06962 0.06612 -0.1308 0.7133 0.0429
-7.250 0.2569 0.06873 0.06494 -0.1285 0.6650 0.0433
-7.000 0.2609 0.06747 0.06352 -0.1273 0.6330 0.0438
-6.750 0.1444 0.02250 0.01783 -0.1805 0.6779 0.0364
-6.500 0.1667 0.02020 0.01491 -0.1824 0.6465 0.0368
-6.250 0.1909 0.01892 0.01316 -0.1830 0.6208 0.0373
-6.000 0.2144 0.01764 0.01155 -0.1831 0.5992 0.0378
-5.750 0.2386 0.01703 0.01079 -0.1828 0.5804 0.0384
-5.500 0.2636 0.01661 0.01021 -0.1825 0.5642 0.0390
-5.000 0.3150 0.01584 0.00910 -0.1818 0.5385 0.0408
-4.750 0.3411 0.01554 0.00856 -0.1815 0.5285 0.0419
-4.500 0.3670 0.01489 0.00780 -0.1812 0.5198 0.0427
-4.250 0.3924 0.01460 0.00742 -0.1807 0.5116 0.0437
-4.000 0.4193 0.01432 0.00709 -0.1804 0.5052 0.0448
-3.750 0.4458 0.01409 0.00675 -0.1800 0.4988 0.0461
-3.500 0.4719 0.01398 0.00648 -0.1795 0.4927 0.0472
-3.250 0.4983 0.01355 0.00606 -0.1792 0.4880 0.0489
-3.000 0.5251 0.01341 0.00589 -0.1788 0.4829 0.0508
-2.750 0.5516 0.01333 0.00570 -0.1784 0.4782 0.0527
-2.500 0.5772 0.01312 0.00543 -0.1779 0.4737 0.0548
-2.250 0.6043 0.01299 0.00530 -0.1775 0.4704 0.0572
-2.000 0.6313 0.01284 0.00512 -0.1772 0.4671 0.0600
-1.750 0.6579 0.01272 0.00500 -0.1768 0.4637 0.0638
-1.500 0.6844 0.01263 0.00486 -0.1764 0.4604 0.0681
-1.250 0.7107 0.01263 0.00481 -0.1759 0.4568 0.0734
-1.000 0.7372 0.01261 0.00477 -0.1755 0.4533 0.0816
-0.750 0.7640 0.01250 0.00471 -0.1751 0.4510 0.0946
-0.500 0.7908 0.01243 0.00470 -0.1748 0.4485 0.1157
-0.250 0.8173 0.01239 0.00474 -0.1744 0.4459 0.1407
0.000 0.8438 0.01243 0.00478 -0.1740 0.4432 0.1611
0.250 0.8701 0.01249 0.00485 -0.1735 0.4404 0.1802
0.500 0.8965 0.01262 0.00496 -0.1731 0.4375 0.1979
0.750 0.9235 0.01277 0.00510 -0.1729 0.4348 0.2156
1.000 0.9497 0.01279 0.00518 -0.1724 0.4328 0.2336
1.250 0.9759 0.01283 0.00526 -0.1719 0.4305 0.2519
1.500 1.0020 0.01288 0.00535 -0.1715 0.4281 0.2710
1.750 1.0279 0.01295 0.00545 -0.1710 0.4257 0.2928
2.250 1.0795 0.01315 0.00570 -0.1700 0.4209 0.3424
2.500 1.1061 0.01335 0.00591 -0.1698 0.4181 0.3702
2.750 1.1323 0.01348 0.00609 -0.1694 0.4160 0.4004
3.000 1.1573 0.01351 0.00623 -0.1687 0.4142 0.4332
3.250 1.1823 0.01358 0.00639 -0.1681 0.4122 0.4682
3.500 1.2073 0.01366 0.00657 -0.1675 0.4101 0.5074
3.750 1.2320 0.01376 0.00675 -0.1668 0.4081 0.5492
4.000 1.2564 0.01386 0.00692 -0.1661 0.4060 0.5922
4.250 1.2806 0.01397 0.00711 -0.1654 0.4039 0.6371
4.500 1.3052 0.01413 0.00733 -0.1647 0.4015 0.6859
4.750 1.3319 0.01432 0.00761 -0.1646 0.3986 0.7530
5.000 1.3883 0.01429 0.00787 -0.1708 0.3966 1.0000
5.250 1.4134 0.01446 0.00804 -0.1704 0.3948 1.0000
5.500 1.4385 0.01465 0.00822 -0.1699 0.3927 1.0000
5.750 1.4635 0.01484 0.00841 -0.1694 0.3906 1.0000
6.000 1.4883 0.01505 0.00860 -0.1689 0.3885 1.0000
6.250 1.5129 0.01527 0.00880 -0.1684 0.3864 1.0000
6.500 1.5380 0.01554 0.00903 -0.1680 0.3842 1.0000
6.750 1.5661 0.01597 0.00939 -0.1682 0.3812 1.0000
7.000 1.5882 0.01614 0.00962 -0.1673 0.3797 1.0000
7.250 1.6096 0.01633 0.00984 -0.1662 0.3776 1.0000
7.500 1.6308 0.01654 0.01009 -0.1651 0.3753 1.0000
7.750 1.6523 0.01676 0.01033 -0.1641 0.3730 1.0000
8.000 1.6738 0.01700 0.01057 -0.1631 0.3708 1.0000
8.250 1.6955 0.01726 0.01084 -0.1621 0.3686 1.0000
8.500 1.7186 0.01760 0.01114 -0.1615 0.3662 1.0000
8.750 1.7437 0.01800 0.01153 -0.1613 0.3636 1.0000
9.000 1.7619 0.01826 0.01187 -0.1599 0.3618 1.0000
9.250 1.7806 0.01855 0.01222 -0.1585 0.3594 1.0000
9.500 1.7998 0.01886 0.01258 -0.1574 0.3569 1.0000
9.750 1.8190 0.01918 0.01293 -0.1562 0.3544 1.0000
10.000 1.8383 0.01953 0.01330 -0.1551 0.3520 1.0000
10.250 1.8588 0.01994 0.01369 -0.1543 0.3496 1.0000
10.500 1.8806 0.02040 0.01415 -0.1536 0.3469 1.0000
10.750 1.8967 0.02084 0.01469 -0.1522 0.3448 1.0000
11.000 1.9133 0.02129 0.01523 -0.1509 0.3423 1.0000
11.250 1.9300 0.02177 0.01576 -0.1496 0.3397 1.0000
11.500 1.9463 0.02226 0.01629 -0.1483 0.3370 1.0000
11.750 1.9632 0.02279 0.01683 -0.1471 0.3344 1.0000
12.000 1.9806 0.02338 0.01740 -0.1460 0.3310 1.0000
12.250 1.9911 0.02409 0.01824 -0.1442 0.3277 1.0000
12.500 2.0024 0.02482 0.01905 -0.1425 0.3236 1.0000
12.750 2.0140 0.02560 0.01985 -0.1409 0.3197 1.0000
13.000 2.0272 0.02641 0.02062 -0.1395 0.3159 1.0000
13.250 2.0381 0.02732 0.02166 -0.1380 0.3129 1.0000
13.500 2.0498 0.02822 0.02266 -0.1366 0.3096 1.0000
13.750 2.0609 0.02919 0.02369 -0.1352 0.3065 1.0000
14.000 2.0710 0.03024 0.02476 -0.1337 0.3035 1.0000
14.250 2.0804 0.03136 0.02589 -0.1322 0.3000 1.0000
14.500 2.0892 0.03258 0.02724 -0.1308 0.2972 1.0000
14.750 2.0975 0.03386 0.02862 -0.1294 0.2939 1.0000
15.000 2.1043 0.03527 0.03008 -0.1279 0.2903 1.0000
15.250 2.1083 0.03692 0.03173 -0.1263 0.2865 1.0000
15.500 2.1127 0.03868 0.03360 -0.1250 0.2826 1.0000
15.750 2.1160 0.04061 0.03563 -0.1238 0.2781 1.0000
16.000 2.1164 0.04284 0.03789 -0.1225 0.2736 1.0000
16.250 2.1160 0.04520 0.04030 -0.1212 0.2695 1.0000
16.500 2.1172 0.04759 0.04282 -0.1203 0.2655 1.0000
16.750 2.1147 0.05036 0.04566 -0.1193 0.2610 1.0000
17.000 2.1082 0.05357 0.04887 -0.1183 0.2565 1.0000
17.250 2.1054 0.05656 0.05201 -0.1176 0.2526 1.0000
17.500 2.0981 0.06008 0.05563 -0.1170 0.2477 1.0000
17.750 2.0858 0.06418 0.05974 -0.1163 0.2428 1.0000
18.000 2.0752 0.06824 0.06392 -0.1159 0.2378 1.0000
18.250 2.0604 0.07285 0.06862 -0.1156 0.2321 1.0000
18.500 2.0411 0.07797 0.07376 -0.1153 0.2264 1.0000
18.750 2.0232 0.08315 0.07908 -0.1153 0.2200 1.0000
19.000 1.9996 0.08901 0.08495 -0.1153 0.2135 1.0000
19.250 1.9788 0.09464 0.09069 -0.1156 0.2061 1.0000
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