UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 100,000 Max Cl/Cd: 17.54 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ui1720-il-100000.txt Download as CSV file: xf-ui1720-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2829 0.11968 0.11359 -0.0083 0.4648 0.1010
-9.500 -0.2799 0.11713 0.11098 -0.0107 0.4542 0.1051
-9.250 -0.3055 0.11662 0.11063 -0.0190 0.4595 0.1069
-9.000 -0.2662 0.11030 0.10406 -0.0137 0.4363 0.1095
-8.750 -0.2538 0.10758 0.10120 -0.0139 0.4283 0.1142
-8.500 -0.2720 0.10649 0.10022 -0.0212 0.4292 0.1189
-8.250 -0.2509 0.10148 0.09515 -0.0188 0.4197 0.1212
-8.000 -0.2339 0.09855 0.09211 -0.0178 0.4129 0.1251
-7.750 -0.2388 0.09660 0.09018 -0.0227 0.4113 0.1317
-7.500 -0.2339 0.09271 0.08625 -0.0246 0.4082 0.1345
-7.250 -0.2117 0.08988 0.08339 -0.0221 0.4027 0.1394
-7.000 -0.2290 0.08746 0.08106 -0.0411 0.4046 0.1480
-6.750 -0.2086 0.08387 0.07744 -0.0297 0.3986 0.1501
-6.500 -0.1896 0.08163 0.07512 -0.0268 0.3945 0.1560
-6.250 -0.1860 0.07745 0.07094 -0.0393 0.3937 0.1655
-6.000 -0.1684 0.07543 0.06882 -0.0335 0.3903 0.1693
-5.750 -0.1542 0.07137 0.06465 -0.0456 0.3889 0.1829
-5.500 -0.1305 0.06881 0.06192 -0.0562 0.3871 0.1996
-5.250 -0.1181 0.06559 0.05886 -0.0495 0.3846 0.2015
-5.000 -0.1021 0.06398 0.05730 -0.0446 0.3822 0.2064
-4.750 -0.0799 0.06058 0.05380 -0.0512 0.3804 0.2217
-4.500 -0.0609 0.05899 0.05221 -0.0494 0.3784 0.2306
-4.250 -0.0044 0.04263 0.03465 -0.0777 0.3776 0.1664
-4.000 0.0249 0.03910 0.03079 -0.0800 0.3758 0.1577
-3.750 0.0554 0.03584 0.02703 -0.0825 0.3741 0.1550
-3.500 0.0851 0.03377 0.02453 -0.0837 0.3726 0.1548
-3.250 0.1142 0.03246 0.02287 -0.0844 0.3711 0.1565
-3.000 0.1433 0.03144 0.02150 -0.0848 0.3697 0.1578
-2.750 0.1723 0.03069 0.02048 -0.0851 0.3684 0.1608
-2.500 0.2014 0.03005 0.01959 -0.0851 0.3671 0.1631
-2.250 0.2295 0.02936 0.01881 -0.0851 0.3658 0.1657
-2.000 0.2569 0.02907 0.01857 -0.0849 0.3645 0.1702
-1.750 0.2847 0.02895 0.01842 -0.0847 0.3636 0.1753
-1.500 0.3128 0.02892 0.01827 -0.0845 0.3629 0.1803
-1.250 0.3397 0.02880 0.01828 -0.0843 0.3624 0.1865
-1.000 0.3668 0.02901 0.01853 -0.0840 0.3619 0.1958
-0.750 0.3933 0.02916 0.01881 -0.0837 0.3617 0.2060
-0.500 0.4197 0.02947 0.01922 -0.0834 0.3615 0.2206
-0.250 0.4454 0.02983 0.01981 -0.0831 0.3616 0.2426
0.000 0.4708 0.03024 0.02051 -0.0828 0.3618 0.2800
0.250 0.4953 0.03062 0.02137 -0.0825 0.3622 0.3579
0.500 0.5185 0.03095 0.02246 -0.0819 0.3628 0.5143
0.750 0.5336 0.03108 0.02352 -0.0790 0.3633 0.7527
1.000 0.5610 0.03198 0.02460 -0.0790 0.3635 0.9996
1.250 0.5852 0.03344 0.02599 -0.0791 0.3638 0.9996
1.500 0.6088 0.03508 0.02757 -0.0792 0.3649 0.9996
1.750 0.6320 0.03681 0.02925 -0.0793 0.3662 0.9996
2.000 0.6554 0.03858 0.03094 -0.0794 0.3675 0.9996
2.250 0.6795 0.04039 0.03262 -0.0794 0.3687 0.9996
2.500 0.5680 0.06787 0.06203 -0.1091 0.4753 0.9996
2.750 0.5980 0.06953 0.06352 -0.1083 0.4722 0.9996
3.000 0.6330 0.07147 0.06531 -0.1074 0.4705 0.9996
3.250 0.6658 0.07391 0.06760 -0.1059 0.4694 0.9996
3.500 0.6342 0.07601 0.06969 -0.1068 0.4516 0.9996
3.750 0.6693 0.07820 0.07175 -0.1058 0.4501 0.9996
4.000 0.7023 0.08120 0.07463 -0.1049 0.4487 0.9996
4.250 0.6640 0.08277 0.07619 -0.1054 0.4314 0.9996
4.500 0.6984 0.08519 0.07851 -0.1045 0.4300 0.9996
4.750 0.7359 0.08808 0.08133 -0.1035 0.4291 0.9996
5.000 0.6825 0.08994 0.08318 -0.1046 0.4120 0.9996
5.250 0.7136 0.09242 0.08559 -0.1038 0.4104 0.9996
5.500 0.7506 0.09544 0.08853 -0.1028 0.4093 0.9996
5.750 0.6979 0.09735 0.09045 -0.1041 0.3933 0.9996
6.000 0.7264 0.09973 0.09277 -0.1032 0.3912 0.9996
6.250 0.7593 0.10268 0.09566 -0.1024 0.3899 0.9996
6.500 0.7962 0.10638 0.09932 -0.1014 0.3891 0.9996
6.750 0.7302 0.10753 0.10049 -0.1035 0.3732 0.9996
7.000 0.7577 0.11016 0.10307 -0.1026 0.3713 0.9996
7.250 0.7912 0.11340 0.10627 -0.1017 0.3701 0.9996
7.500 0.8297 0.11760 0.11044 -0.1007 0.3693 0.9996
7.750 0.7584 0.11803 0.11090 -0.1033 0.3537 0.9996
8.000 0.7834 0.12080 0.11364 -0.1026 0.3518 0.9996
8.250 0.8133 0.12419 0.11700 -0.1018 0.3507 0.9996
8.500 0.8484 0.12846 0.12126 -0.1008 0.3499 0.9996
8.750 0.7794 0.12890 0.12173 -0.1039 0.3355 0.9996
9.000 0.8016 0.13158 0.12439 -0.1033 0.3333 0.9996
9.250 0.8284 0.13486 0.12766 -0.1026 0.3319 0.9996
9.500 0.8596 0.13895 0.13175 -0.1018 0.3310 0.9996
9.750 0.7987 0.14006 0.13289 -0.1054 0.3196 0.9996
10.000 0.8145 0.14253 0.13536 -0.1051 0.3163 0.9996
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Polar data table (+)
Polar graphs
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