UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Reynolds number: 1,000,000 Max Cl/Cd: 139.55 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ua2-180-il-1000000-n5.txt Download as CSV file: xf-ua2-180-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: UA(2)-180 (University of Alberta/Marsden)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0864 0.09120 0.08707 -0.1000 0.4985 0.0098
-10.000 0.0896 0.08808 0.08396 -0.1011 0.4982 0.0098
-9.750 0.0932 0.08511 0.08102 -0.1022 0.4976 0.0096
-9.500 0.0982 0.08249 0.07841 -0.1032 0.4971 0.0101
-9.250 0.0994 0.07927 0.07521 -0.1043 0.4966 0.0098
-9.000 0.1000 0.07603 0.07200 -0.1054 0.4961 0.0098
-8.750 0.0996 0.07276 0.06875 -0.1066 0.4955 0.0099
-8.500 0.0972 0.06930 0.06533 -0.1078 0.4951 0.0097
-8.250 0.0919 0.06557 0.06163 -0.1092 0.4945 0.0096
-8.000 0.0838 0.06169 0.05779 -0.1109 0.4940 0.0097
-7.750 0.0636 0.05713 0.05329 -0.1136 0.4936 0.0096
-7.500 0.0433 0.05279 0.04893 -0.1144 0.4931 0.0097
-7.250 0.0271 0.04716 0.04322 -0.1152 0.4926 0.0096
-7.000 0.0219 0.04270 0.03864 -0.1148 0.4921 0.0098
-6.750 0.0172 0.03782 0.03356 -0.1133 0.4916 0.0101
-6.500 0.0126 0.03255 0.02799 -0.1108 0.4910 0.0102
-6.250 -0.0244 0.02045 0.01472 -0.1025 0.4909 0.0111
-6.000 -0.0032 0.01957 0.01370 -0.1016 0.4899 0.0112
-5.750 0.0197 0.01892 0.01293 -0.1009 0.4889 0.0113
-5.500 0.0438 0.01851 0.01243 -0.1003 0.4877 0.0115
-5.250 0.0666 0.01772 0.01150 -0.0995 0.4864 0.0116
-5.000 0.0907 0.01710 0.01079 -0.0989 0.4853 0.0117
-4.750 0.1154 0.01649 0.01008 -0.0984 0.4846 0.0120
-4.500 0.1400 0.01574 0.00922 -0.0978 0.4839 0.0123
-4.250 0.1644 0.01484 0.00819 -0.0971 0.4831 0.0126
-4.000 0.1889 0.01397 0.00720 -0.0964 0.4820 0.0130
-3.750 0.2140 0.01334 0.00647 -0.0958 0.4810 0.0133
-3.500 0.2398 0.01291 0.00597 -0.0954 0.4796 0.0136
-3.250 0.2651 0.01247 0.00548 -0.0949 0.4784 0.0138
-3.000 0.2916 0.01224 0.00524 -0.0947 0.4771 0.0141
-2.750 0.3183 0.01208 0.00506 -0.0944 0.4761 0.0143
-2.500 0.3453 0.01198 0.00495 -0.0943 0.4752 0.0147
-2.250 0.3720 0.01183 0.00478 -0.0941 0.4743 0.0151
-2.000 0.3980 0.01160 0.00452 -0.0937 0.4734 0.0155
-1.750 0.4238 0.01139 0.00427 -0.0933 0.4724 0.0159
-1.500 0.4498 0.01122 0.00407 -0.0929 0.4712 0.0163
-1.250 0.4761 0.01107 0.00389 -0.0926 0.4700 0.0166
-1.000 0.5022 0.01086 0.00369 -0.0923 0.4692 0.0170
-0.750 0.5289 0.01074 0.00358 -0.0921 0.4683 0.0175
-0.500 0.5558 0.01065 0.00350 -0.0919 0.4674 0.0180
-0.250 0.5828 0.01057 0.00342 -0.0918 0.4665 0.0186
0.000 0.6098 0.01051 0.00336 -0.0917 0.4656 0.0196
0.250 0.6367 0.01044 0.00328 -0.0915 0.4646 0.0201
0.500 0.6631 0.01033 0.00318 -0.0913 0.4634 0.0207
0.750 0.6898 0.01026 0.00311 -0.0911 0.4621 0.0214
1.000 0.7165 0.01021 0.00306 -0.0910 0.4606 0.0222
1.250 0.7431 0.01018 0.00302 -0.0908 0.4590 0.0233
1.500 0.7694 0.01015 0.00298 -0.0906 0.4574 0.0246
1.750 0.7954 0.01013 0.00295 -0.0903 0.4558 0.0257
2.000 0.8221 0.01011 0.00295 -0.0902 0.4545 0.0272
2.250 0.8491 0.01010 0.00295 -0.0902 0.4533 0.0284
2.500 0.8758 0.01009 0.00295 -0.0901 0.4519 0.0311
2.750 0.9025 0.01009 0.00297 -0.0900 0.4504 0.0350
3.000 0.9229 0.00958 0.00305 -0.0889 0.4489 0.3061
3.250 0.9363 0.00883 0.00317 -0.0864 0.4476 0.6453
3.500 1.0028 0.00832 0.00348 -0.0949 0.4457 0.9631
3.750 1.0506 0.00846 0.00359 -0.0994 0.4437 0.9782
4.000 1.0891 0.00860 0.00369 -0.1019 0.4418 0.9873
4.250 1.1317 0.00875 0.00381 -0.1054 0.4395 0.9946
5.000 1.2393 0.00900 0.00404 -0.1115 0.4306 1.0000
5.250 1.2594 0.00912 0.00412 -0.1102 0.4261 1.0000
5.500 1.2806 0.00922 0.00422 -0.1092 0.4222 1.0000
5.750 1.3014 0.00934 0.00432 -0.1080 0.4159 1.0000
6.000 1.3210 0.00948 0.00444 -0.1067 0.4112 1.0000
6.250 1.3411 0.00961 0.00457 -0.1055 0.4066 1.0000
6.500 1.3602 0.00978 0.00471 -0.1041 0.3990 1.0000
6.750 1.3772 0.00999 0.00489 -0.1023 0.3901 1.0000
7.000 1.3895 0.01035 0.00517 -0.0997 0.3740 1.0000
7.250 1.3935 0.01081 0.00554 -0.0955 0.3569 1.0000
7.500 1.3974 0.01123 0.00590 -0.0913 0.3463 1.0000
7.750 1.4036 0.01168 0.00631 -0.0877 0.3373 1.0000
8.000 1.4149 0.01206 0.00667 -0.0851 0.3316 1.0000
8.250 1.4262 0.01248 0.00709 -0.0827 0.3257 1.0000
8.500 1.4329 0.01311 0.00769 -0.0797 0.3179 1.0000
8.750 1.4491 0.01346 0.00806 -0.0783 0.3149 1.0000
9.000 1.4640 0.01389 0.00852 -0.0768 0.3111 1.0000
9.250 1.4759 0.01447 0.00911 -0.0750 0.3065 1.0000
9.500 1.4848 0.01524 0.00988 -0.0729 0.3011 1.0000
9.750 1.4970 0.01593 0.01058 -0.0714 0.2939 1.0000
10.000 1.5044 0.01692 0.01157 -0.0696 0.2869 1.0000
10.250 1.5080 0.01824 0.01288 -0.0676 0.2747 1.0000
10.500 1.5066 0.02002 0.01463 -0.0654 0.2635 1.0000
10.750 1.4951 0.02270 0.01728 -0.0628 0.2505 1.0000
11.000 1.4836 0.02561 0.02019 -0.0607 0.2418 1.0000
11.250 1.4803 0.02811 0.02272 -0.0594 0.2371 1.0000
11.500 1.4795 0.03054 0.02521 -0.0584 0.2345 1.0000
11.750 1.4708 0.03370 0.02841 -0.0572 0.2304 1.0000
12.000 1.4699 0.03614 0.03091 -0.0563 0.2289 1.0000
12.250 1.4650 0.03896 0.03378 -0.0552 0.2261 1.0000
12.500 1.4654 0.04131 0.03618 -0.0545 0.2241 1.0000
12.750 1.4690 0.04337 0.03829 -0.0538 0.2233 1.0000
13.000 1.4700 0.04562 0.04059 -0.0531 0.2198 1.0000
13.250 1.4709 0.04792 0.04294 -0.0525 0.2179 1.0000
13.500 1.4712 0.05025 0.04529 -0.0518 0.2149 1.0000
13.750 1.4679 0.05298 0.04805 -0.0510 0.2114 1.0000
14.000 1.4698 0.05522 0.05031 -0.0505 0.2083 1.0000
14.250 1.4792 0.05677 0.05191 -0.0502 0.2068 1.0000
14.500 1.4835 0.05883 0.05400 -0.0499 0.2022 1.0000
14.750 1.4867 0.06100 0.05619 -0.0495 0.1983 1.0000
15.000 1.4878 0.06338 0.05856 -0.0490 0.1934 1.0000
15.250 1.4941 0.06527 0.06048 -0.0488 0.1882 1.0000
15.500 1.4856 0.06873 0.06389 -0.0483 0.1755 1.0000
15.750 1.4760 0.07228 0.06735 -0.0477 0.1610 1.0000
16.000 1.4717 0.07538 0.07043 -0.0473 0.1542 1.0000
16.250 1.4717 0.07801 0.07306 -0.0471 0.1478 1.0000
16.500 1.4708 0.08075 0.07579 -0.0469 0.1419 1.0000
16.750 1.4735 0.08316 0.07823 -0.0468 0.1387 1.0000
17.000 1.4764 0.08551 0.08061 -0.0468 0.1341 1.0000
17.250 1.4733 0.08854 0.08362 -0.0466 0.1267 1.0000
17.500 1.4689 0.09179 0.08685 -0.0466 0.1162 1.0000
17.750 1.4448 0.09739 0.09228 -0.0464 0.0911 1.0000
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Polar data table (+)
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