FX 72-LS-160 (fx72ls160-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 72-LS-160 (fx72ls160-il) Reynolds number: 500,000 Max Cl/Cd: 121.16 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72ls160-il-500000.txt Download as CSV file: xf-fx72ls160-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.1888 0.10276 0.09843 -0.1368 0.6810 0.0165
-10.750 0.1964 0.10013 0.09582 -0.1381 0.6802 0.0169
-10.500 0.1986 0.09718 0.09290 -0.1401 0.6793 0.0172
-10.250 0.2024 0.09416 0.08991 -0.1415 0.6783 0.0174
-10.000 0.2150 0.09194 0.08770 -0.1419 0.6772 0.0175
-9.750 0.2243 0.08969 0.08547 -0.1428 0.6760 0.0177
-9.500 0.2337 0.08759 0.08338 -0.1436 0.6747 0.0180
-9.250 0.2416 0.08530 0.08110 -0.1445 0.6734 0.0185
-9.000 0.2491 0.08298 0.07879 -0.1454 0.6721 0.0190
-8.750 0.2544 0.08037 0.07619 -0.1467 0.6710 0.0198
-8.500 0.2478 0.07663 0.07250 -0.1496 0.6699 0.0203
-8.250 0.2547 0.07408 0.06996 -0.1503 0.6687 0.0204
-8.000 0.2681 0.07245 0.06832 -0.1502 0.6676 0.0206
-7.750 0.2760 0.07039 0.06626 -0.1509 0.6664 0.0208
-7.500 0.2845 0.06854 0.06441 -0.1514 0.6648 0.0215
-7.250 0.2895 0.06632 0.06222 -0.1522 0.6635 0.0221
-6.750 0.2691 0.05889 0.05496 -0.1570 0.6613 0.0236
-6.500 0.2791 0.05729 0.05338 -0.1572 0.6601 0.0238
-6.250 0.2888 0.05531 0.05142 -0.1585 0.6588 0.0241
-6.000 0.2992 0.05315 0.04927 -0.1603 0.6574 0.0249
-5.750 0.3094 0.04989 0.04599 -0.1638 0.6560 0.0258
-5.500 0.3179 0.04292 0.03888 -0.1709 0.6545 0.0274
-5.250 0.3351 0.04144 0.03736 -0.1716 0.6531 0.0279
-5.000 0.3346 0.02431 0.01900 -0.1774 0.6521 0.0207
-4.750 0.3570 0.01913 0.01286 -0.1781 0.6510 0.0178
-4.500 0.3846 0.01836 0.01196 -0.1785 0.6498 0.0182
-4.250 0.4128 0.01774 0.01117 -0.1789 0.6487 0.0191
-4.000 0.4409 0.01697 0.01017 -0.1792 0.6472 0.0195
-3.750 0.4684 0.01624 0.00927 -0.1793 0.6459 0.0195
-3.500 0.4962 0.01561 0.00855 -0.1795 0.6448 0.0198
-3.250 0.5240 0.01515 0.00803 -0.1796 0.6434 0.0202
-3.000 0.5518 0.01466 0.00755 -0.1799 0.6420 0.0210
-2.750 0.5801 0.01439 0.00728 -0.1802 0.6406 0.0220
-2.500 0.6087 0.01416 0.00703 -0.1805 0.6392 0.0232
-2.250 0.6374 0.01394 0.00680 -0.1809 0.6379 0.0248
-2.000 0.6665 0.01378 0.00662 -0.1813 0.6366 0.0276
-1.750 0.6959 0.01359 0.00643 -0.1818 0.6353 0.0318
-1.500 0.7258 0.01337 0.00629 -0.1824 0.6340 0.0560
-1.250 0.7554 0.01329 0.00624 -0.1830 0.6327 0.0750
-1.000 0.7851 0.01329 0.00623 -0.1836 0.6315 0.0899
-0.750 0.8143 0.01339 0.00635 -0.1842 0.6299 0.1081
-0.500 0.8424 0.01333 0.00642 -0.1846 0.6287 0.1429
-0.250 0.8709 0.01312 0.00649 -0.1852 0.6275 0.2335
0.000 0.9006 0.01272 0.00665 -0.1864 0.6260 0.4359
0.250 0.9267 0.01204 0.00697 -0.1865 0.6246 0.7849
0.500 0.9396 0.01203 0.00715 -0.1830 0.6230 0.8942
0.750 0.9550 0.01205 0.00718 -0.1802 0.6214 0.9327
1.000 0.9690 0.01198 0.00711 -0.1771 0.6198 0.9600
1.250 0.9985 0.01191 0.00699 -0.1775 0.6184 0.9969
1.500 1.0292 0.01199 0.00700 -0.1783 0.6172 1.0000
1.750 1.0598 0.01209 0.00703 -0.1792 0.6160 1.0000
2.000 1.0906 0.01223 0.00710 -0.1802 0.6148 1.0000
2.250 1.1208 0.01253 0.00733 -0.1810 0.6132 1.0000
2.500 1.1481 0.01268 0.00749 -0.1814 0.6119 1.0000
2.750 1.1749 0.01283 0.00766 -0.1816 0.6103 1.0000
3.000 1.2020 0.01297 0.00782 -0.1819 0.6084 1.0000
3.250 1.2296 0.01311 0.00795 -0.1823 0.6066 1.0000
3.500 1.2577 0.01323 0.00808 -0.1827 0.6050 1.0000
3.750 1.2863 0.01335 0.00818 -0.1833 0.6035 1.0000
4.000 1.3155 0.01345 0.00827 -0.1839 0.6021 1.0000
4.250 1.3451 0.01355 0.00834 -0.1847 0.6009 1.0000
4.500 1.3752 0.01365 0.00842 -0.1855 0.5996 1.0000
4.750 1.4057 0.01379 0.00853 -0.1864 0.5982 1.0000
5.000 1.4328 0.01406 0.00881 -0.1868 0.5965 1.0000
5.250 1.4559 0.01428 0.00912 -0.1864 0.5947 1.0000
5.500 1.4798 0.01451 0.00940 -0.1862 0.5927 1.0000
5.750 1.5047 0.01469 0.00962 -0.1862 0.5907 1.0000
6.000 1.5309 0.01481 0.00977 -0.1863 0.5888 1.0000
6.250 1.5587 0.01488 0.00986 -0.1868 0.5871 1.0000
6.500 1.5882 0.01486 0.00983 -0.1875 0.5853 1.0000
6.750 1.6194 0.01482 0.00976 -0.1885 0.5834 1.0000
7.000 1.6481 0.01498 0.00993 -0.1891 0.5813 1.0000
7.250 1.6652 0.01523 0.01030 -0.1877 0.5786 1.0000
7.500 1.6856 0.01537 0.01052 -0.1868 0.5756 1.0000
7.750 1.7101 0.01538 0.01056 -0.1866 0.5728 1.0000
8.000 1.7389 0.01517 0.01034 -0.1871 0.5697 1.0000
8.250 1.7691 0.01503 0.01017 -0.1878 0.5661 1.0000
8.500 1.7768 0.01525 0.01052 -0.1846 0.5615 1.0000
8.750 1.7926 0.01520 0.01050 -0.1827 0.5565 1.0000
9.000 1.8174 0.01500 0.01025 -0.1824 0.5513 1.0000
9.250 1.8123 0.01547 0.01085 -0.1770 0.5459 1.0000
9.500 1.8215 0.01577 0.01120 -0.1743 0.5408 1.0000
9.750 1.8426 0.01589 0.01129 -0.1736 0.5362 1.0000
10.000 1.8381 0.01677 0.01231 -0.1691 0.5303 1.0000
10.250 1.8461 0.01734 0.01290 -0.1666 0.5238 1.0000
10.500 1.8480 0.01832 0.01395 -0.1635 0.5171 1.0000
10.750 1.8497 0.01940 0.01505 -0.1605 0.5090 1.0000
11.000 1.8477 0.02086 0.01659 -0.1574 0.5007 1.0000
11.250 1.8501 0.02218 0.01789 -0.1549 0.4919 1.0000
11.500 1.8442 0.02421 0.02002 -0.1519 0.4828 1.0000
11.750 1.8425 0.02604 0.02186 -0.1493 0.4733 1.0000
12.000 1.8369 0.02823 0.02406 -0.1465 0.4620 1.0000
12.250 1.8280 0.03081 0.02668 -0.1437 0.4492 1.0000
12.500 1.8184 0.03356 0.02943 -0.1409 0.4345 1.0000
12.750 1.8052 0.03669 0.03251 -0.1380 0.4169 1.0000
13.000 1.7908 0.04008 0.03585 -0.1352 0.3974 1.0000
13.250 1.7737 0.04387 0.03955 -0.1323 0.3755 1.0000
13.500 1.7550 0.04795 0.04352 -0.1296 0.3545 1.0000
13.750 1.7408 0.05180 0.04729 -0.1274 0.3341 1.0000
14.000 1.7285 0.05559 0.05100 -0.1255 0.3138 1.0000
14.250 1.7163 0.05950 0.05484 -0.1238 0.2946 1.0000
14.500 1.7039 0.06359 0.05884 -0.1223 0.2756 1.0000
14.750 1.6957 0.06729 0.06248 -0.1210 0.2563 1.0000
15.000 1.6870 0.07118 0.06630 -0.1200 0.2382 1.0000
15.250 1.6793 0.07502 0.07007 -0.1190 0.2200 1.0000
15.500 1.6717 0.07893 0.07391 -0.1182 0.2026 1.0000
16.000 1.6588 0.08671 0.08155 -0.1171 0.1684 1.0000
16.250 1.6536 0.09054 0.08532 -0.1168 0.1521 1.0000
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Polar data table (+)
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