FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-CL3-152 (fx73cl3152-il) Reynolds number: 100,000 Max Cl/Cd: 38.44 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl3152-il-100000.txt Download as CSV file: xf-fx73cl3152-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0236 0.12402 0.11948 -0.0663 0.9588 0.0883
-9.250 -0.0068 0.12117 0.11663 -0.0721 0.9515 0.0915
-9.000 -0.0022 0.11999 0.11547 -0.0801 0.9430 0.0928
-8.750 0.0482 0.11202 0.10745 -0.0828 0.9409 0.0951
-8.500 0.0708 0.10853 0.10396 -0.0857 0.9310 0.0983
-8.250 0.0832 0.10740 0.10281 -0.0961 0.9244 0.1032
-8.000 0.1122 0.10166 0.09708 -0.0982 0.9157 0.1047
-7.750 0.1537 0.09637 0.09175 -0.1026 0.9107 0.1078
-7.500 0.1876 0.09236 0.08769 -0.1097 0.9057 0.1129
-7.250 0.1650 0.09412 0.08950 -0.1135 0.8811 0.1156
-7.000 0.2109 0.08681 0.08215 -0.1148 0.8748 0.1176
-6.750 0.2394 0.08308 0.07839 -0.1162 0.8622 0.1209
-6.500 0.2523 0.08077 0.07604 -0.1174 0.8446 0.1256
-6.250 0.2241 0.08236 0.07765 -0.1184 0.8173 0.1290
-6.000 0.2464 0.07752 0.07277 -0.1169 0.8009 0.1311
-5.750 0.2728 0.07413 0.06929 -0.1161 0.7822 0.1352
-5.500 0.2784 0.07248 0.06757 -0.1156 0.7619 0.1397
-5.250 0.2702 0.07219 0.06720 -0.1237 0.7426 0.1450
-5.000 0.2903 0.06847 0.06336 -0.1193 0.7267 0.1467
-4.750 0.3091 0.06606 0.06082 -0.1180 0.7114 0.1503
-4.500 0.3237 0.06517 0.05974 -0.1321 0.6977 0.1611
-4.250 0.3376 0.06196 0.05642 -0.1268 0.6863 0.1626
-4.000 0.3521 0.06007 0.05446 -0.1235 0.6739 0.1659
-3.750 0.3799 0.05795 0.05213 -0.1348 0.6642 0.1794
-3.500 0.3900 0.05604 0.05022 -0.1301 0.6537 0.1816
-3.250 0.4706 0.03704 0.03010 -0.1694 0.6484 0.1162
-3.000 0.5033 0.03346 0.02609 -0.1738 0.6393 0.1151
-2.750 0.5386 0.03029 0.02234 -0.1776 0.6316 0.1150
-2.500 0.5705 0.02829 0.01989 -0.1796 0.6250 0.1173
-2.250 0.5953 0.02794 0.01958 -0.1793 0.6174 0.1223
-2.000 0.6282 0.02661 0.01768 -0.1806 0.6112 0.1275
-1.750 0.6562 0.02593 0.01681 -0.1809 0.6052 0.1337
-1.500 0.6821 0.02561 0.01632 -0.1806 0.5985 0.1426
-1.250 0.7105 0.02522 0.01584 -0.1807 0.5930 0.1525
-1.000 0.7413 0.02499 0.01541 -0.1811 0.5887 0.1672
-0.750 0.7639 0.02500 0.01549 -0.1803 0.5834 0.1840
-0.500 0.7889 0.02506 0.01559 -0.1798 0.5781 0.2066
-0.250 0.8171 0.02510 0.01550 -0.1797 0.5735 0.2371
0.000 0.8468 0.02526 0.01565 -0.1798 0.5696 0.2674
0.250 0.8677 0.02564 0.01613 -0.1787 0.5647 0.2949
0.500 0.8904 0.02599 0.01659 -0.1779 0.5602 0.3215
0.750 0.9152 0.02628 0.01693 -0.1773 0.5561 0.3491
1.000 0.9435 0.02652 0.01706 -0.1772 0.5523 0.3791
1.250 0.9688 0.02690 0.01750 -0.1767 0.5487 0.4058
1.500 0.9871 0.02746 0.01822 -0.1753 0.5442 0.4317
1.750 1.0096 0.02795 0.01878 -0.1745 0.5401 0.4616
2.000 1.0356 0.02831 0.01917 -0.1742 0.5362 0.4964
2.250 1.0651 0.02861 0.01945 -0.1743 0.5328 0.5370
2.500 1.0905 0.02917 0.02007 -0.1738 0.5294 0.5796
2.750 1.1044 0.03006 0.02120 -0.1720 0.5251 0.6214
3.000 1.1242 0.03068 0.02198 -0.1709 0.5209 0.6767
3.250 1.1525 0.03074 0.02223 -0.1711 0.5171 0.7685
3.500 1.1864 0.03086 0.02232 -0.1723 0.5137 1.0000
3.750 1.2167 0.03167 0.02291 -0.1730 0.5108 1.0000
4.000 1.2200 0.03344 0.02485 -0.1702 0.5063 1.0000
4.250 1.2321 0.03483 0.02625 -0.1685 0.5019 1.0000
4.500 1.2557 0.03559 0.02692 -0.1680 0.4982 1.0000
4.750 1.2855 0.03607 0.02726 -0.1683 0.4951 1.0000
5.000 1.3192 0.03660 0.02761 -0.1691 0.4925 1.0000
5.250 1.2950 0.04002 0.03137 -0.1633 0.4874 1.0000
5.500 1.2701 0.04363 0.03518 -0.1579 0.4819 1.0000
5.750 1.2888 0.04468 0.03618 -0.1569 0.4784 1.0000
6.000 1.3348 0.04418 0.03553 -0.1587 0.4760 1.0000
6.250 1.3783 0.04404 0.03523 -0.1604 0.4738 1.0000
6.500 1.0663 0.07423 0.06637 -0.1409 0.4539 1.0000
6.750 0.8834 0.10220 0.09489 -0.1443 0.4520 1.0000
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Polar data table (+)
Polar graphs
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