FX 73-CL2-152 (fx73cl2152-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 73-CL2-152 (fx73cl2152-il) Reynolds number: 50,000 Max Cl/Cd: 16.34 at α=0° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl2152-il-50000.txt Download as CSV file: xf-fx73cl2152-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL2-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1916 0.13248 0.12625 -0.0254 1.0000 0.1959
-8.500 -0.2177 0.13500 0.12896 -0.0245 1.0000 0.1979
-8.250 -0.2191 0.13215 0.12626 -0.0231 1.0000 0.1994
-8.000 -0.2019 0.12733 0.12152 -0.0209 1.0000 0.2028
-7.750 -0.2076 0.12635 0.12071 -0.0182 1.0000 0.2062
-7.500 -0.2294 0.12762 0.12222 -0.0143 1.0000 0.2080
-7.250 -0.2251 0.12790 0.12258 -0.0213 0.9898 0.2156
-7.000 -0.1779 0.12098 0.11563 -0.0288 0.9771 0.2221
-6.750 -0.1466 0.11765 0.11226 -0.0368 0.9594 0.2334
-6.500 -0.1212 0.11358 0.10819 -0.0443 0.9423 0.2388
-6.250 -0.0748 0.10783 0.10237 -0.0500 0.9275 0.2489
-6.000 -0.0980 0.11059 0.10518 -0.0550 0.9004 0.2559
-5.750 -0.0172 0.09993 0.09441 -0.0607 0.8953 0.2694
-5.500 -0.0487 0.10291 0.09745 -0.0625 0.8684 0.2760
-5.250 0.0294 0.09293 0.08735 -0.0679 0.8638 0.2877
-5.000 0.0069 0.09459 0.08907 -0.0711 0.8446 0.2968
-4.750 0.0668 0.08698 0.08135 -0.0726 0.8356 0.3075
-4.500 0.0891 0.08370 0.07802 -0.0770 0.8261 0.3214
-4.250 0.0971 0.08244 0.07673 -0.0779 0.8106 0.3354
-4.000 0.1270 0.07836 0.07259 -0.0799 0.8001 0.3444
-3.750 0.1433 0.07629 0.07047 -0.0847 0.7899 0.3599
-3.500 0.1630 0.07383 0.06798 -0.0829 0.7783 0.3711
-3.250 0.2041 0.05832 0.05181 -0.1294 0.7693 0.2163
-3.000 0.1880 0.05955 0.05319 -0.1214 0.7558 0.2202
-2.750 0.3273 0.04594 0.03858 -0.1567 0.7517 0.2138
-2.500 0.3640 0.04376 0.03614 -0.1619 0.7412 0.2220
-2.250 0.4335 0.04066 0.03264 -0.1711 0.7339 0.2432
-2.000 0.4773 0.03951 0.03129 -0.1751 0.7263 0.2674
-1.750 0.5134 0.03890 0.03046 -0.1782 0.7173 0.2986
-1.500 0.5609 0.03812 0.02965 -0.1803 0.7114 0.3421
-1.250 0.5590 0.03961 0.03118 -0.1771 0.7018 0.3608
-1.000 0.5916 0.03969 0.03122 -0.1774 0.6953 0.3995
-0.750 0.6221 0.03977 0.03133 -0.1764 0.6903 0.4321
-0.500 0.6023 0.04256 0.03418 -0.1724 0.6811 0.4402
-0.250 0.6269 0.04287 0.03453 -0.1712 0.6753 0.4661
0.000 0.6846 0.04191 0.03336 -0.1748 0.6709 0.5033
0.250 0.6015 0.04842 0.04019 -0.1646 0.6616 0.4848
0.500 0.6264 0.04915 0.04089 -0.1647 0.6562 0.5084
0.750 0.7033 0.04710 0.03864 -0.1695 0.6522 0.5524
1.000 0.5971 0.05691 0.04874 -0.1611 0.6452 0.5246
1.250 0.5834 0.06083 0.05272 -0.1599 0.6410 0.5328
1.500 0.6093 0.06218 0.05399 -0.1611 0.6362 0.5594
1.750 0.6757 0.05988 0.05159 -0.1621 0.6312 0.6057
2.000 0.6359 0.06629 0.05812 -0.1605 0.6297 0.6037
2.250 0.6244 0.07044 0.06230 -0.1602 0.6288 0.6170
2.500 0.6197 0.07381 0.06575 -0.1595 0.6286 0.6337
2.750 0.6260 0.07671 0.06870 -0.1596 0.6297 0.6591
3.000 0.6401 0.07923 0.07127 -0.1598 0.6312 0.6947
3.250 0.4634 0.09355 0.08609 -0.1605 0.7773 0.5927
3.500 0.4965 0.09613 0.08865 -0.1622 0.7706 0.6331
3.750 0.5003 0.09734 0.08991 -0.1608 0.7591 0.6596
4.000 0.5306 0.09962 0.09225 -0.1616 0.7514 0.7147
4.250 0.5308 0.10049 0.09325 -0.1592 0.7393 0.7541
4.500 0.5444 0.10117 0.09418 -0.1561 0.7324 0.8524
4.750 0.5529 0.10228 0.09523 -0.1572 0.7197 1.0000
5.000 0.6059 0.10689 0.09938 -0.1644 0.7122 1.0000
5.250 0.6093 0.10860 0.10096 -0.1642 0.6996 1.0000
5.500 0.6496 0.11252 0.10462 -0.1675 0.6924 1.0000
5.750 0.6485 0.11397 0.10600 -0.1665 0.6795 1.0000
6.000 0.6839 0.11771 0.10956 -0.1688 0.6730 1.0000
6.250 0.6813 0.11936 0.11117 -0.1679 0.6622 1.0000
6.500 0.7102 0.12257 0.11425 -0.1694 0.6544 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 73-CL2-152 (fx73cl2152-il)