UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Reynolds number: 500,000 Max Cl/Cd: 106.99 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ua2-180-il-500000-n5.txt Download as CSV file: xf-ua2-180-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0769 0.09867 0.09373 -0.0946 0.5138 0.0162
-10.250 0.0744 0.09477 0.08985 -0.0969 0.5133 0.0166
-10.000 0.0754 0.09118 0.08629 -0.0985 0.5128 0.0166
-9.750 0.0807 0.08840 0.08353 -0.0996 0.5122 0.0166
-9.500 0.0845 0.08536 0.08051 -0.1007 0.5116 0.0166
-9.250 0.0876 0.08230 0.07746 -0.1019 0.5110 0.0167
-9.000 0.0891 0.07898 0.07417 -0.1032 0.5104 0.0167
-8.750 0.0898 0.07559 0.07081 -0.1046 0.5098 0.0167
-8.500 0.0915 0.07255 0.06780 -0.1057 0.5092 0.0167
-8.250 0.0923 0.06946 0.06474 -0.1069 0.5085 0.0166
-7.250 0.0528 0.05402 0.04936 -0.1122 0.5064 0.0134
-7.000 0.0447 0.04937 0.04461 -0.1129 0.5059 0.0134
-6.750 0.0383 0.04438 0.03945 -0.1125 0.5053 0.0135
-6.500 0.0411 0.04102 0.03593 -0.1115 0.5048 0.0134
-6.250 0.0449 0.03749 0.03218 -0.1101 0.5041 0.0134
-6.000 0.0441 0.03223 0.02647 -0.1073 0.5036 0.0137
-5.750 0.0578 0.03052 0.02459 -0.1060 0.5029 0.0139
-5.500 0.0759 0.02943 0.02339 -0.1052 0.5021 0.0140
-5.250 0.0961 0.02866 0.02251 -0.1045 0.5013 0.0142
-5.000 0.1144 0.02716 0.02084 -0.1034 0.5007 0.0144
-4.750 0.1318 0.02518 0.01861 -0.1018 0.5002 0.0145
-4.500 0.1515 0.02361 0.01681 -0.1006 0.4996 0.0147
-4.250 0.1727 0.02224 0.01521 -0.0994 0.4989 0.0149
-4.000 0.1951 0.02102 0.01379 -0.0984 0.4982 0.0151
-3.750 0.2184 0.01993 0.01250 -0.0975 0.4971 0.0155
-3.500 0.2426 0.01893 0.01131 -0.0967 0.4958 0.0159
-3.250 0.2676 0.01804 0.01025 -0.0961 0.4945 0.0162
-3.000 0.2931 0.01731 0.00931 -0.0954 0.4931 0.0168
-2.750 0.3187 0.01677 0.00874 -0.0951 0.4919 0.0171
-2.500 0.3448 0.01648 0.00842 -0.0949 0.4910 0.0175
-2.250 0.3710 0.01608 0.00798 -0.0945 0.4901 0.0180
-2.000 0.3971 0.01566 0.00750 -0.0942 0.4892 0.0183
-1.750 0.4230 0.01527 0.00705 -0.0938 0.4881 0.0188
-1.500 0.4490 0.01493 0.00665 -0.0934 0.4870 0.0194
-1.250 0.4750 0.01468 0.00632 -0.0930 0.4860 0.0199
-1.000 0.5006 0.01440 0.00604 -0.0926 0.4850 0.0203
-0.750 0.5259 0.01414 0.00582 -0.0922 0.4843 0.0210
-0.500 0.5519 0.01400 0.00569 -0.0919 0.4834 0.0219
-0.250 0.5776 0.01383 0.00553 -0.0915 0.4823 0.0228
0.000 0.6034 0.01367 0.00537 -0.0912 0.4812 0.0236
0.250 0.6291 0.01353 0.00522 -0.0908 0.4798 0.0242
0.500 0.6545 0.01335 0.00507 -0.0904 0.4788 0.0250
0.750 0.6804 0.01325 0.00498 -0.0901 0.4778 0.0259
1.000 0.7066 0.01318 0.00491 -0.0899 0.4767 0.0276
1.250 0.7326 0.01310 0.00482 -0.0896 0.4756 0.0289
1.500 0.7586 0.01302 0.00473 -0.0893 0.4744 0.0304
1.750 0.7848 0.01299 0.00469 -0.0891 0.4734 0.0320
2.000 0.8109 0.01296 0.00464 -0.0889 0.4724 0.0350
2.250 0.8371 0.01296 0.00462 -0.0887 0.4713 0.0396
2.500 0.8558 0.01226 0.00470 -0.0874 0.4702 0.3632
2.750 0.8624 0.01125 0.00486 -0.0835 0.4693 0.7509
3.250 1.0291 0.01135 0.00539 -0.1071 0.4656 0.9960
3.500 1.0726 0.01143 0.00545 -0.1107 0.4640 1.0000
3.750 1.0943 0.01150 0.00551 -0.1097 0.4623 1.0000
4.000 1.1160 0.01157 0.00556 -0.1087 0.4606 1.0000
4.250 1.1376 0.01163 0.00560 -0.1077 0.4588 1.0000
4.500 1.1593 0.01172 0.00567 -0.1068 0.4574 1.0000
4.750 1.1809 0.01180 0.00572 -0.1057 0.4559 1.0000
5.000 1.2023 0.01191 0.00583 -0.1048 0.4541 1.0000
5.250 1.2239 0.01202 0.00597 -0.1038 0.4521 1.0000
5.500 1.2455 0.01213 0.00611 -0.1029 0.4502 1.0000
5.750 1.2668 0.01224 0.00624 -0.1019 0.4482 1.0000
6.000 1.2878 0.01235 0.00636 -0.1008 0.4461 1.0000
6.250 1.3084 0.01246 0.00647 -0.0997 0.4441 1.0000
6.500 1.3281 0.01256 0.00656 -0.0984 0.4417 1.0000
6.750 1.3477 0.01269 0.00668 -0.0972 0.4395 1.0000
7.000 1.3674 0.01283 0.00688 -0.0959 0.4360 1.0000
7.250 1.3857 0.01296 0.00704 -0.0945 0.4319 1.0000
7.500 1.4015 0.01310 0.00718 -0.0925 0.4277 1.0000
7.750 1.4141 0.01326 0.00732 -0.0899 0.4241 1.0000
8.000 1.4292 0.01343 0.00755 -0.0879 0.4190 1.0000
8.250 1.4422 0.01364 0.00777 -0.0855 0.4136 1.0000
8.500 1.4547 0.01390 0.00802 -0.0832 0.4085 1.0000
8.750 1.4696 0.01418 0.00833 -0.0814 0.4021 1.0000
9.000 1.4798 0.01458 0.00872 -0.0789 0.3943 1.0000
9.250 1.4896 0.01506 0.00921 -0.0766 0.3835 1.0000
9.500 1.4927 0.01584 0.00994 -0.0735 0.3698 1.0000
9.750 1.4933 0.01688 0.01093 -0.0703 0.3583 1.0000
10.000 1.4877 0.01840 0.01240 -0.0669 0.3463 1.0000
10.250 1.4858 0.01997 0.01396 -0.0643 0.3383 1.0000
10.500 1.4861 0.02158 0.01559 -0.0623 0.3321 1.0000
10.750 1.4885 0.02319 0.01723 -0.0607 0.3269 1.0000
11.000 1.4873 0.02514 0.01921 -0.0590 0.3220 1.0000
11.250 1.4846 0.02731 0.02141 -0.0574 0.3174 1.0000
11.500 1.4868 0.02925 0.02342 -0.0563 0.3118 1.0000
11.750 1.4795 0.03210 0.02631 -0.0549 0.3051 1.0000
12.000 1.4743 0.03481 0.02905 -0.0537 0.2996 1.0000
12.250 1.4704 0.03748 0.03177 -0.0527 0.2914 1.0000
12.500 1.4604 0.04073 0.03505 -0.0516 0.2838 1.0000
12.750 1.4504 0.04406 0.03838 -0.0505 0.2731 1.0000
13.000 1.4343 0.04797 0.04226 -0.0493 0.2615 1.0000
13.250 1.4276 0.05100 0.04530 -0.0484 0.2564 1.0000
13.500 1.4192 0.05421 0.04849 -0.0475 0.2483 1.0000
13.750 1.4159 0.05699 0.05127 -0.0469 0.2437 1.0000
14.000 1.4183 0.05919 0.05348 -0.0464 0.2400 1.0000
14.250 1.4241 0.06108 0.05541 -0.0460 0.2371 1.0000
14.500 1.4293 0.06306 0.05743 -0.0457 0.2342 1.0000
14.750 1.4340 0.06508 0.05948 -0.0454 0.2312 1.0000
15.000 1.4403 0.06693 0.06135 -0.0451 0.2287 1.0000
15.250 1.4448 0.06896 0.06338 -0.0448 0.2256 1.0000
15.500 1.4521 0.07079 0.06527 -0.0447 0.2229 1.0000
15.750 1.4578 0.07278 0.06733 -0.0445 0.2186 1.0000
16.000 1.4645 0.07466 0.06924 -0.0444 0.2154 1.0000
16.250 1.4690 0.07676 0.07136 -0.0442 0.2117 1.0000
16.500 1.4719 0.07908 0.07370 -0.0441 0.2083 1.0000
16.750 1.4803 0.08083 0.07553 -0.0441 0.2052 1.0000
17.000 1.4858 0.08289 0.07764 -0.0441 0.2000 1.0000
17.250 1.4841 0.08577 0.08052 -0.0441 0.1929 1.0000
17.500 1.4890 0.08793 0.08275 -0.0441 0.1874 1.0000
17.750 1.4832 0.09138 0.08616 -0.0441 0.1757 1.0000
18.000 1.4743 0.09522 0.08997 -0.0442 0.1655 1.0000
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Polar data table (+)
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