FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 72-LS-160 (fx72ls160-il) Reynolds number: 200,000 Max Cl/Cd: 58.48 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx72ls160-il-200000-n5.txt Download as CSV file: xf-fx72ls160-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 72-LS-160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.2007 0.09711 0.09135 -0.1369 0.6811 0.0268
-9.750 0.2062 0.09464 0.08893 -0.1382 0.6797 0.0269
-9.500 0.2090 0.09212 0.08645 -0.1397 0.6783 0.0270
-9.250 0.2158 0.08944 0.08382 -0.1406 0.6770 0.0271
-9.000 0.2263 0.08709 0.08148 -0.1410 0.6757 0.0273
-8.750 0.2356 0.08485 0.07926 -0.1415 0.6743 0.0276
-8.500 0.2423 0.08250 0.07694 -0.1424 0.6730 0.0277
-8.250 0.2482 0.08009 0.07456 -0.1433 0.6716 0.0279
-7.250 0.2499 0.06665 0.06118 -0.1479 0.6662 0.0172
-7.000 0.2513 0.06420 0.05875 -0.1485 0.6650 0.0171
-6.750 0.2503 0.06210 0.05667 -0.1490 0.6639 0.0169
-6.500 0.2511 0.05934 0.05398 -0.1511 0.6625 0.0167
-6.250 0.2542 0.05614 0.05082 -0.1540 0.6609 0.0165
-6.000 0.2520 0.04909 0.04373 -0.1608 0.6590 0.0173
-5.750 0.2595 0.04355 0.03805 -0.1648 0.6573 0.0173
-5.500 0.2681 0.03677 0.03094 -0.1682 0.6556 0.0172
-5.250 0.2823 0.03146 0.02511 -0.1701 0.6541 0.0169
-5.000 0.3022 0.02720 0.02017 -0.1714 0.6527 0.0169
-4.750 0.3266 0.02462 0.01701 -0.1720 0.6515 0.0170
-4.500 0.3529 0.02300 0.01494 -0.1723 0.6503 0.0173
-4.250 0.3800 0.02212 0.01389 -0.1727 0.6491 0.0177
-4.000 0.4077 0.02140 0.01299 -0.1730 0.6479 0.0182
-3.750 0.4358 0.02075 0.01216 -0.1734 0.6468 0.0189
-3.500 0.4612 0.02028 0.01158 -0.1732 0.6451 0.0200
-3.250 0.4860 0.02004 0.01134 -0.1731 0.6433 0.0214
-3.000 0.5115 0.01977 0.01101 -0.1729 0.6416 0.0230
-2.750 0.5375 0.01948 0.01069 -0.1729 0.6399 0.0241
-2.500 0.5640 0.01926 0.01043 -0.1730 0.6383 0.0256
-2.250 0.5911 0.01903 0.01015 -0.1731 0.6367 0.0278
-2.000 0.6189 0.01880 0.00990 -0.1733 0.6352 0.0321
-1.750 0.6472 0.01860 0.00970 -0.1736 0.6338 0.0423
-1.500 0.6757 0.01848 0.00960 -0.1740 0.6325 0.0607
-1.250 0.7045 0.01841 0.00953 -0.1745 0.6315 0.0777
-1.000 0.7336 0.01835 0.00946 -0.1750 0.6305 0.0927
-0.750 0.7625 0.01832 0.00942 -0.1755 0.6295 0.1120
-0.500 0.7842 0.01847 0.00975 -0.1749 0.6273 0.1403
-0.250 0.8074 0.01853 0.01002 -0.1747 0.6250 0.1925
0.000 0.8324 0.01844 0.01025 -0.1749 0.6229 0.2967
0.250 0.8589 0.01812 0.01048 -0.1753 0.6210 0.4881
0.500 0.8732 0.01768 0.01080 -0.1725 0.6194 0.7455
0.750 0.8787 0.01765 0.01094 -0.1674 0.6179 0.8871
1.000 0.8955 0.01765 0.01092 -0.1650 0.6166 0.9472
1.250 0.9282 0.01767 0.01084 -0.1662 0.6155 1.0000
1.500 0.9579 0.01780 0.01086 -0.1668 0.6145 1.0000
1.750 0.9883 0.01793 0.01086 -0.1676 0.6135 1.0000
2.000 1.0045 0.01851 0.01148 -0.1662 0.6107 1.0000
2.250 1.0198 0.01912 0.01211 -0.1647 0.6076 1.0000
2.500 1.0403 0.01955 0.01252 -0.1639 0.6053 1.0000
2.750 1.0634 0.01988 0.01282 -0.1636 0.6035 1.0000
3.000 1.0884 0.02014 0.01304 -0.1635 0.6019 1.0000
3.250 1.1150 0.02034 0.01319 -0.1637 0.6006 1.0000
3.500 1.1431 0.02047 0.01328 -0.1641 0.5995 1.0000
3.750 1.1733 0.02055 0.01330 -0.1648 0.5985 1.0000
4.000 1.2047 0.02060 0.01330 -0.1658 0.5975 1.0000
4.250 1.1686 0.02284 0.01576 -0.1566 0.5904 1.0000
4.500 1.1774 0.02364 0.01659 -0.1542 0.5875 1.0000
4.750 1.1986 0.02399 0.01693 -0.1537 0.5858 1.0000
5.000 1.2251 0.02413 0.01705 -0.1538 0.5846 1.0000
5.250 1.2547 0.02414 0.01705 -0.1544 0.5835 1.0000
5.500 1.2860 0.02411 0.01700 -0.1553 0.5826 1.0000
5.750 1.3185 0.02409 0.01697 -0.1563 0.5819 1.0000
6.250 1.2559 0.03000 0.02308 -0.1431 0.5675 1.0000
6.500 1.2870 0.02981 0.02289 -0.1437 0.5669 1.0000
8.500 1.2963 0.04577 0.03923 -0.1288 0.5221 1.0000
9.000 1.2972 0.05041 0.04398 -0.1258 0.5082 1.0000
9.250 1.3268 0.04990 0.04349 -0.1260 0.5074 1.0000
9.500 1.3577 0.04925 0.04289 -0.1263 0.5068 1.0000
10.500 1.3735 0.05738 0.05128 -0.1216 0.4789 1.0000
11.000 1.3905 0.06068 0.05471 -0.1201 0.4655 1.0000
11.250 1.4195 0.06006 0.05416 -0.1202 0.4636 1.0000
11.500 1.4524 0.05900 0.05315 -0.1205 0.4619 1.0000
12.000 1.4785 0.06123 0.05551 -0.1193 0.4466 1.0000
12.500 1.4802 0.06645 0.06087 -0.1174 0.4231 1.0000
12.750 1.5129 0.06527 0.05971 -0.1176 0.4168 1.0000
13.000 1.5199 0.06720 0.06169 -0.1169 0.4044 1.0000
13.250 1.5390 0.06764 0.06214 -0.1166 0.3922 1.0000
13.500 1.5635 0.06731 0.06174 -0.1164 0.3752 1.0000
13.750 1.5842 0.06731 0.06156 -0.1160 0.3517 1.0000
14.000 1.5904 0.06912 0.06322 -0.1151 0.3271 1.0000
14.250 1.5919 0.07158 0.06555 -0.1142 0.3056 1.0000
14.500 1.5911 0.07448 0.06839 -0.1134 0.2864 1.0000
14.750 1.5896 0.07751 0.07135 -0.1126 0.2680 1.0000
15.000 1.5865 0.08082 0.07460 -0.1120 0.2502 1.0000
15.250 1.5832 0.08423 0.07795 -0.1114 0.2329 1.0000
15.500 1.5789 0.08783 0.08149 -0.1109 0.2162 1.0000
15.750 1.5757 0.09136 0.08499 -0.1106 0.2005 1.0000
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