FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.31 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-1000000.txt Download as CSV file: xf-fx73cl3152-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.1808 0.09133 0.08874 -0.1260 0.8303 0.0262
-10.000 -0.1325 0.03891 0.03604 -0.1553 0.8336 0.0253
-9.750 -0.1609 0.02589 0.02259 -0.1746 0.8253 0.0254
-9.500 -0.1389 0.02000 0.01628 -0.1854 0.8174 0.0257
-9.250 -0.1144 0.01854 0.01468 -0.1870 0.8099 0.0260
-9.000 -0.0883 0.01772 0.01380 -0.1878 0.8002 0.0263
-8.750 -0.0620 0.01708 0.01307 -0.1882 0.7891 0.0266
-8.500 -0.0361 0.01647 0.01233 -0.1884 0.7724 0.0270
-8.250 -0.0116 0.01584 0.01150 -0.1883 0.7420 0.0273
-8.000 0.0101 0.01543 0.01078 -0.1876 0.6941 0.0277
-7.750 0.0328 0.01503 0.01011 -0.1870 0.6564 0.0280
-7.500 0.0568 0.01467 0.00952 -0.1865 0.6274 0.0283
-7.250 0.0820 0.01430 0.00897 -0.1862 0.6040 0.0286
-7.000 0.1077 0.01402 0.00851 -0.1859 0.5833 0.0289
-6.750 0.1330 0.01349 0.00780 -0.1856 0.5650 0.0293
-6.500 0.1583 0.01301 0.00719 -0.1854 0.5486 0.0298
-6.250 0.1847 0.01277 0.00686 -0.1851 0.5343 0.0303
-6.000 0.2115 0.01257 0.00658 -0.1848 0.5225 0.0309
-5.750 0.2379 0.01240 0.00630 -0.1844 0.5110 0.0314
-5.500 0.2651 0.01219 0.00601 -0.1842 0.5021 0.0321
-5.250 0.2917 0.01206 0.00577 -0.1838 0.4925 0.0327
-5.000 0.3192 0.01191 0.00554 -0.1835 0.4860 0.0330
-4.750 0.3455 0.01153 0.00510 -0.1832 0.4790 0.0342
-4.500 0.3722 0.01143 0.00494 -0.1828 0.4721 0.0350
-4.250 0.3999 0.01130 0.00478 -0.1826 0.4674 0.0359
-4.000 0.4270 0.01120 0.00461 -0.1822 0.4621 0.0368
-3.750 0.4537 0.01112 0.00444 -0.1818 0.4564 0.0376
-3.500 0.4805 0.01090 0.00420 -0.1814 0.4525 0.0389
-3.250 0.5081 0.01080 0.00408 -0.1812 0.4494 0.0402
-3.000 0.5354 0.01073 0.00396 -0.1808 0.4459 0.0414
-2.750 0.5622 0.01063 0.00381 -0.1804 0.4424 0.0429
-2.500 0.5888 0.01058 0.00373 -0.1800 0.4386 0.0448
-2.250 0.6154 0.01058 0.00369 -0.1795 0.4349 0.0467
-2.000 0.6428 0.01045 0.00356 -0.1792 0.4330 0.0490
-1.750 0.6702 0.01039 0.00349 -0.1789 0.4307 0.0517
-1.500 0.6972 0.01032 0.00341 -0.1785 0.4281 0.0551
-1.250 0.7240 0.01031 0.00337 -0.1781 0.4255 0.0590
-1.000 0.7503 0.01027 0.00333 -0.1776 0.4229 0.0652
-0.750 0.7763 0.01028 0.00333 -0.1770 0.4199 0.0738
-0.500 0.8019 0.01028 0.00336 -0.1764 0.4167 0.0898
-0.250 0.8289 0.01020 0.00336 -0.1761 0.4154 0.1118
0.000 0.8558 0.01018 0.00338 -0.1757 0.4137 0.1303
0.250 0.8826 0.01017 0.00341 -0.1753 0.4118 0.1470
0.500 0.9091 0.01018 0.00345 -0.1749 0.4096 0.1629
1.000 0.9610 0.01027 0.00357 -0.1738 0.4049 0.1953
1.250 0.9862 0.01035 0.00367 -0.1732 0.4022 0.2120
1.500 1.0109 0.01049 0.00380 -0.1725 0.3989 0.2279
1.750 1.0373 0.01051 0.00386 -0.1720 0.3978 0.2447
2.000 1.0635 0.01053 0.00393 -0.1716 0.3965 0.2620
2.250 1.0894 0.01056 0.00402 -0.1711 0.3950 0.2843
2.500 1.1151 0.01060 0.00411 -0.1705 0.3934 0.3079
2.750 1.1405 0.01065 0.00421 -0.1699 0.3917 0.3316
3.000 1.1655 0.01071 0.00431 -0.1693 0.3898 0.3575
3.250 1.1900 0.01079 0.00443 -0.1685 0.3877 0.3844
3.500 1.2137 0.01090 0.00457 -0.1677 0.3854 0.4119
3.750 1.2369 0.01105 0.00475 -0.1667 0.3827 0.4416
4.000 1.2603 0.01117 0.00492 -0.1658 0.3807 0.4738
4.250 1.2838 0.01119 0.00505 -0.1649 0.3797 0.5111
4.500 1.3067 0.01123 0.00518 -0.1638 0.3784 0.5483
4.750 1.3294 0.01129 0.00532 -0.1628 0.3769 0.5865
5.000 1.3520 0.01137 0.00548 -0.1617 0.3753 0.6255
5.250 1.3743 0.01145 0.00564 -0.1606 0.3736 0.6681
5.500 1.3958 0.01153 0.00581 -0.1593 0.3718 0.7152
5.750 1.4901 0.01158 0.00622 -0.1739 0.3684 1.0000
6.000 1.5138 0.01184 0.00645 -0.1732 0.3656 1.0000
6.250 1.5385 0.01206 0.00665 -0.1727 0.3634 1.0000
6.500 1.5641 0.01218 0.00679 -0.1724 0.3621 1.0000
6.750 1.5893 0.01233 0.00695 -0.1719 0.3604 1.0000
7.000 1.6141 0.01249 0.00713 -0.1715 0.3586 1.0000
7.250 1.6384 0.01267 0.00731 -0.1710 0.3566 1.0000
7.500 1.6621 0.01287 0.00752 -0.1703 0.3545 1.0000
7.750 1.6849 0.01312 0.00775 -0.1696 0.3522 1.0000
8.000 1.7065 0.01343 0.00804 -0.1687 0.3494 1.0000
8.250 1.7288 0.01372 0.00833 -0.1679 0.3469 1.0000
8.500 1.7526 0.01389 0.00855 -0.1674 0.3452 1.0000
8.750 1.7759 0.01410 0.00878 -0.1668 0.3431 1.0000
9.000 1.7986 0.01434 0.00905 -0.1662 0.3408 1.0000
9.250 1.8203 0.01462 0.00934 -0.1654 0.3384 1.0000
9.500 1.8408 0.01496 0.00968 -0.1644 0.3358 1.0000
9.750 1.8596 0.01540 0.01010 -0.1633 0.3326 1.0000
10.000 1.8805 0.01574 0.01047 -0.1624 0.3304 1.0000
10.250 1.9023 0.01601 0.01080 -0.1618 0.3284 1.0000
10.500 1.9235 0.01632 0.01115 -0.1610 0.3258 1.0000
10.750 1.9431 0.01672 0.01156 -0.1600 0.3226 1.0000
11.000 1.9603 0.01723 0.01206 -0.1588 0.3189 1.0000
11.250 1.9776 0.01775 0.01259 -0.1576 0.3147 1.0000
11.500 1.9981 0.01811 0.01299 -0.1569 0.3107 1.0000
11.750 2.0155 0.01863 0.01353 -0.1558 0.3064 1.0000
12.000 2.0298 0.01934 0.01423 -0.1543 0.3019 1.0000
12.250 2.0470 0.01989 0.01482 -0.1532 0.2987 1.0000
12.500 2.0650 0.02041 0.01538 -0.1522 0.2952 1.0000
12.750 2.0804 0.02107 0.01607 -0.1510 0.2918 1.0000
13.000 2.0930 0.02192 0.01692 -0.1494 0.2880 1.0000
13.250 2.1065 0.02273 0.01776 -0.1480 0.2845 1.0000
13.500 2.1222 0.02339 0.01849 -0.1469 0.2819 1.0000
13.750 2.1359 0.02420 0.01933 -0.1456 0.2781 1.0000
14.000 2.1451 0.02532 0.02046 -0.1439 0.2735 1.0000
14.250 2.1549 0.02642 0.02158 -0.1424 0.2692 1.0000
14.500 2.1674 0.02734 0.02255 -0.1411 0.2648 1.0000
14.750 2.1747 0.02866 0.02389 -0.1394 0.2604 1.0000
15.000 2.1783 0.03029 0.02554 -0.1375 0.2557 1.0000
15.250 2.1903 0.03133 0.02666 -0.1364 0.2526 1.0000
15.500 2.1969 0.03282 0.02818 -0.1349 0.2480 1.0000
15.750 2.1967 0.03494 0.03032 -0.1331 0.2427 1.0000
16.000 2.2029 0.03659 0.03203 -0.1318 0.2384 1.0000
16.250 2.2044 0.03871 0.03419 -0.1304 0.2326 1.0000
16.500 2.1980 0.04166 0.03716 -0.1287 0.2268 1.0000
16.750 2.1998 0.04392 0.03948 -0.1276 0.2208 1.0000
17.000 2.1892 0.04753 0.04312 -0.1262 0.2141 1.0000
17.250 2.1834 0.05072 0.04637 -0.1251 0.2074 1.0000
17.500 2.1652 0.05540 0.05108 -0.1239 0.2003 1.0000
17.750 2.1499 0.05987 0.05560 -0.1230 0.1926 1.0000
18.000 2.1206 0.06606 0.06183 -0.1221 0.1845 1.0000
18.250 2.0919 0.07232 0.06814 -0.1215 0.1758 1.0000
18.500 2.0595 0.07917 0.07505 -0.1211 0.1682 1.0000
18.750 2.0224 0.08674 0.08267 -0.1209 0.1606 1.0000
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