UA(2)-180 smoothed (ua2-180sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: UA(2)-180 smoothed (ua2-180sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.44 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua2-180sm-il-1000000.txt Download as CSV file: xf-ua2-180sm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: UA(2)-180 smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0580 0.09818 0.09417 -0.0987 0.5178 0.0146
-10.750 0.0613 0.09478 0.09079 -0.1001 0.5173 0.0146
-10.500 0.0611 0.09070 0.08673 -0.1014 0.5168 0.0147
-10.250 0.0658 0.08780 0.08384 -0.1023 0.5163 0.0148
-10.000 0.0750 0.08599 0.08205 -0.1026 0.5157 0.0150
-9.750 0.0843 0.08416 0.08022 -0.1030 0.5150 0.0151
-9.500 0.0877 0.08129 0.07737 -0.1040 0.5145 0.0152
-9.250 0.0940 0.07908 0.07517 -0.1047 0.5139 0.0154
-9.000 0.0971 0.07633 0.07244 -0.1056 0.5133 0.0155
-8.750 0.1006 0.07379 0.06991 -0.1065 0.5128 0.0160
-8.500 0.1017 0.07089 0.06704 -0.1076 0.5122 0.0165
-8.250 0.1005 0.06774 0.06391 -0.1088 0.5117 0.0165
-7.000 0.0017 0.03854 0.03435 -0.1143 0.5098 0.0181
-6.750 0.0117 0.03682 0.03255 -0.1133 0.5091 0.0182
-6.500 0.0274 0.03601 0.03171 -0.1126 0.5083 0.0184
-6.250 0.0399 0.03429 0.02989 -0.1115 0.5076 0.0186
-6.000 0.0538 0.03265 0.02812 -0.1104 0.5066 0.0189
-5.750 0.0686 0.03099 0.02632 -0.1093 0.5056 0.0194
-5.500 0.0765 0.02825 0.02289 -0.1054 0.5045 0.0213
-5.250 0.0855 0.02444 0.01888 -0.1036 0.5035 0.0218
-5.000 0.1073 0.02333 0.01773 -0.1030 0.5032 0.0220
-4.750 0.1297 0.02245 0.01681 -0.1024 0.5028 0.0224
-4.500 0.1521 0.02153 0.01579 -0.1017 0.5024 0.0228
-4.250 0.1749 0.02063 0.01477 -0.1009 0.5019 0.0237
-4.000 0.1948 0.01925 0.01297 -0.0991 0.5015 0.0259
-3.750 0.2199 0.01840 0.01215 -0.0988 0.5009 0.0265
-3.500 0.2451 0.01775 0.01145 -0.0984 0.5003 0.0272
-3.250 0.2707 0.01729 0.01085 -0.0979 0.4997 0.0288
-3.000 0.2963 0.01553 0.00882 -0.0968 0.4991 0.0244
-2.750 0.3224 0.01453 0.00774 -0.0963 0.4985 0.0234
-2.500 0.3488 0.01382 0.00695 -0.0958 0.4978 0.0228
-2.250 0.3755 0.01349 0.00659 -0.0956 0.4971 0.0233
-2.000 0.4020 0.01314 0.00621 -0.0953 0.4963 0.0237
-1.750 0.4284 0.01280 0.00585 -0.0949 0.4955 0.0241
-1.500 0.4546 0.01252 0.00555 -0.0946 0.4947 0.0243
-1.250 0.4809 0.01229 0.00530 -0.0943 0.4940 0.0246
-1.000 0.5074 0.01211 0.00511 -0.0940 0.4933 0.0249
-0.750 0.5342 0.01198 0.00496 -0.0938 0.4927 0.0252
-0.500 0.5600 0.01176 0.00473 -0.0934 0.4920 0.0256
-0.250 0.5855 0.01153 0.00449 -0.0930 0.4913 0.0265
0.000 0.6124 0.01146 0.00442 -0.0929 0.4904 0.0275
0.250 0.6395 0.01144 0.00438 -0.0928 0.4893 0.0284
0.500 0.6668 0.01154 0.00446 -0.0928 0.4879 0.0292
0.750 0.6938 0.01153 0.00445 -0.0927 0.4870 0.0301
1.000 0.7204 0.01139 0.00433 -0.0925 0.4863 0.0319
1.250 0.7472 0.01130 0.00425 -0.0923 0.4855 0.0343
1.500 0.7738 0.01122 0.00422 -0.0922 0.4846 0.0445
1.750 0.7852 0.00999 0.00428 -0.0896 0.4838 0.5372
2.000 0.8435 0.00911 0.00455 -0.0961 0.4826 0.9605
2.250 0.8902 0.00925 0.00466 -0.1000 0.4813 0.9816
2.500 0.9479 0.00935 0.00471 -0.1064 0.4800 0.9887
2.750 0.9959 0.00941 0.00472 -0.1108 0.4785 0.9940
3.000 1.0477 0.00940 0.00466 -0.1161 0.4770 0.9975
3.250 1.0921 0.00941 0.00462 -0.1199 0.4754 1.0000
3.500 1.1147 0.00949 0.00467 -0.1191 0.4738 1.0000
3.750 1.1378 0.00968 0.00483 -0.1184 0.4718 1.0000
4.000 1.1599 0.00969 0.00485 -0.1175 0.4711 1.0000
4.250 1.1820 0.00972 0.00489 -0.1166 0.4702 1.0000
4.500 1.2043 0.00975 0.00494 -0.1157 0.4690 1.0000
4.750 1.2267 0.00979 0.00499 -0.1149 0.4678 1.0000
5.000 1.2491 0.00982 0.00503 -0.1140 0.4663 1.0000
5.250 1.2717 0.00986 0.00508 -0.1132 0.4649 1.0000
5.500 1.2943 0.00990 0.00511 -0.1124 0.4635 1.0000
5.750 1.3169 0.00994 0.00515 -0.1116 0.4621 1.0000
6.000 1.3393 0.00999 0.00520 -0.1108 0.4607 1.0000
6.250 1.3617 0.01008 0.00527 -0.1100 0.4588 1.0000
6.500 1.3843 0.01021 0.00539 -0.1093 0.4567 1.0000
6.750 1.4057 0.01024 0.00548 -0.1083 0.4554 1.0000
7.000 1.4274 0.01029 0.00556 -0.1074 0.4537 1.0000
7.250 1.4490 0.01034 0.00563 -0.1065 0.4518 1.0000
7.500 1.4705 0.01038 0.00571 -0.1055 0.4497 1.0000
7.750 1.4916 0.01043 0.00576 -0.1045 0.4475 1.0000
8.000 1.5117 0.01050 0.00583 -0.1033 0.4450 1.0000
8.250 1.5315 0.01061 0.00594 -0.1021 0.4422 1.0000
8.500 1.5519 0.01068 0.00607 -0.1011 0.4396 1.0000
8.750 1.5722 0.01076 0.00619 -0.1000 0.4365 1.0000
9.000 1.5889 0.01085 0.00630 -0.0982 0.4331 1.0000
9.250 1.6022 0.01098 0.00642 -0.0957 0.4296 1.0000
9.500 1.6199 0.01110 0.00659 -0.0942 0.4259 1.0000
9.750 1.6372 0.01124 0.00677 -0.0927 0.4207 1.0000
10.000 1.6509 0.01147 0.00699 -0.0906 0.4154 1.0000
10.250 1.6685 0.01169 0.00724 -0.0892 0.4088 1.0000
10.500 1.6799 0.01207 0.00760 -0.0870 0.4006 1.0000
10.750 1.6939 0.01246 0.00799 -0.0853 0.3914 1.0000
11.000 1.7036 0.01303 0.00855 -0.0830 0.3818 1.0000
11.250 1.7095 0.01382 0.00931 -0.0804 0.3714 1.0000
11.500 1.7149 0.01473 0.01021 -0.0780 0.3611 1.0000
11.750 1.7204 0.01574 0.01122 -0.0758 0.3519 1.0000
12.000 1.7207 0.01714 0.01260 -0.0733 0.3425 1.0000
12.250 1.7231 0.01856 0.01403 -0.0713 0.3338 1.0000
12.500 1.7235 0.02024 0.01573 -0.0695 0.3263 1.0000
12.750 1.7210 0.02223 0.01774 -0.0676 0.3187 1.0000
13.000 1.7168 0.02447 0.02001 -0.0658 0.3113 1.0000
13.250 1.7092 0.02712 0.02270 -0.0641 0.3044 1.0000
13.500 1.6985 0.03020 0.02582 -0.0625 0.2978 1.0000
13.750 1.6839 0.03376 0.02941 -0.0609 0.2902 1.0000
14.000 1.6693 0.03739 0.03308 -0.0594 0.2850 1.0000
14.250 1.6626 0.04032 0.03606 -0.0584 0.2790 1.0000
14.500 1.6490 0.04387 0.03962 -0.0571 0.2739 1.0000
14.750 1.6412 0.04695 0.04273 -0.0561 0.2684 1.0000
15.000 1.6310 0.05025 0.04605 -0.0551 0.2617 1.0000
15.500 1.6254 0.05557 0.05143 -0.0538 0.2528 1.0000
15.750 1.6250 0.05802 0.05390 -0.0533 0.2481 1.0000
16.000 1.6163 0.06129 0.05714 -0.0525 0.2423 1.0000
16.250 1.6232 0.06310 0.05902 -0.0523 0.2391 1.0000
16.500 1.6251 0.06539 0.06133 -0.0520 0.2342 1.0000
16.750 1.6210 0.06831 0.06423 -0.0516 0.2292 1.0000
17.000 1.6260 0.07030 0.06629 -0.0514 0.2259 1.0000
17.250 1.6287 0.07256 0.06856 -0.0512 0.2206 1.0000
17.500 1.6261 0.07537 0.07136 -0.0509 0.2155 1.0000
17.750 1.6278 0.07781 0.07384 -0.0508 0.2100 1.0000
18.000 1.6306 0.08008 0.07614 -0.0507 0.2057 1.0000
18.250 1.6275 0.08298 0.07901 -0.0505 0.2001 1.0000
18.500 1.6300 0.08534 0.08143 -0.0505 0.1946 1.0000
18.750 1.6283 0.08815 0.08425 -0.0505 0.1892 1.0000
19.000 1.6303 0.09057 0.08668 -0.0505 0.1841 1.0000
19.250 1.6296 0.09333 0.08947 -0.0506 0.1788 1.0000
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