UA(2)-180 smoothed (ua2-180sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: UA(2)-180 smoothed (ua2-180sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.34 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ua2-180sm-il-1000000-n5.txt Download as CSV file: xf-ua2-180sm-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0480 0.09856 0.09443 -0.0966 0.4979 0.0083
-11.000 0.0494 0.09488 0.09076 -0.0979 0.4975 0.0085
-10.750 0.0354 0.08809 0.08400 -0.1002 0.4972 0.0091
-10.500 0.0431 0.08605 0.08197 -0.1011 0.4966 0.0092
-10.250 0.0504 0.08391 0.07984 -0.1020 0.4960 0.0093
-10.000 0.0503 0.08046 0.07640 -0.1032 0.4956 0.0093
-9.750 0.0517 0.07737 0.07334 -0.1044 0.4952 0.0094
-9.500 0.0572 0.07511 0.07109 -0.1053 0.4945 0.0096
-9.250 0.0581 0.07213 0.06813 -0.1064 0.4940 0.0097
-9.000 0.0562 0.06880 0.06482 -0.1077 0.4936 0.0099
-8.500 -0.1893 0.02940 0.02475 -0.1120 0.4946 0.0115
-8.250 -0.1799 0.02763 0.02280 -0.1103 0.4939 0.0116
-8.000 -0.1631 0.02670 0.02176 -0.1092 0.4932 0.0117
-7.750 -0.1464 0.02564 0.02057 -0.1080 0.4924 0.0118
-7.500 -0.1289 0.02460 0.01940 -0.1068 0.4916 0.0119
-7.250 -0.1107 0.02356 0.01822 -0.1057 0.4908 0.0120
-7.000 -0.0905 0.02278 0.01732 -0.1048 0.4899 0.0122
-6.750 -0.0710 0.02180 0.01619 -0.1037 0.4890 0.0124
-6.500 -0.0504 0.02085 0.01510 -0.1027 0.4886 0.0127
-6.250 -0.0322 0.01926 0.01327 -0.1013 0.4883 0.0131
-6.000 -0.0123 0.01786 0.01163 -0.1000 0.4879 0.0134
-5.750 0.0097 0.01673 0.01029 -0.0990 0.4875 0.0137
-5.500 0.0333 0.01593 0.00935 -0.0982 0.4870 0.0139
-5.250 0.0581 0.01536 0.00866 -0.0977 0.4865 0.0140
-5.000 0.0824 0.01467 0.00788 -0.0971 0.4859 0.0142
-4.750 0.1079 0.01427 0.00744 -0.0967 0.4853 0.0144
-4.500 0.1340 0.01399 0.00713 -0.0964 0.4846 0.0146
-4.250 0.1602 0.01371 0.00682 -0.0960 0.4839 0.0148
-4.000 0.1868 0.01350 0.00659 -0.0958 0.4833 0.0150
-3.750 0.2131 0.01324 0.00629 -0.0955 0.4827 0.0153
-3.500 0.2392 0.01292 0.00594 -0.0951 0.4821 0.0156
-3.250 0.2654 0.01264 0.00562 -0.0948 0.4814 0.0159
-3.000 0.2915 0.01237 0.00531 -0.0945 0.4808 0.0162
-2.750 0.3176 0.01211 0.00502 -0.0941 0.4802 0.0164
-2.500 0.3439 0.01191 0.00479 -0.0938 0.4795 0.0167
-2.250 0.3703 0.01173 0.00458 -0.0935 0.4789 0.0169
-2.000 0.3968 0.01157 0.00440 -0.0932 0.4783 0.0171
-1.750 0.4222 0.01130 0.00412 -0.0927 0.4776 0.0174
-1.500 0.4483 0.01114 0.00396 -0.0924 0.4770 0.0177
-1.250 0.4747 0.01102 0.00383 -0.0922 0.4763 0.0181
-1.000 0.5013 0.01094 0.00374 -0.0920 0.4755 0.0185
-0.750 0.5279 0.01086 0.00365 -0.0918 0.4745 0.0191
-0.500 0.5545 0.01081 0.00358 -0.0915 0.4735 0.0196
-0.250 0.5813 0.01074 0.00351 -0.0914 0.4729 0.0201
0.000 0.6084 0.01067 0.00344 -0.0913 0.4725 0.0204
0.250 0.6351 0.01058 0.00336 -0.0911 0.4721 0.0208
0.500 0.6619 0.01050 0.00329 -0.0910 0.4717 0.0214
0.750 0.6889 0.01045 0.00325 -0.0909 0.4711 0.0221
1.000 0.7160 0.01041 0.00322 -0.0908 0.4702 0.0231
1.250 0.7430 0.01036 0.00319 -0.0907 0.4689 0.0240
1.500 0.7699 0.01032 0.00315 -0.0906 0.4676 0.0252
1.750 0.7969 0.01028 0.00312 -0.0905 0.4662 0.0267
2.250 0.8429 0.00961 0.00316 -0.0891 0.4639 0.3241
2.500 0.8590 0.00896 0.00323 -0.0872 0.4627 0.5989
2.750 0.8673 0.00831 0.00333 -0.0831 0.4615 0.8529
3.250 1.0000 0.00855 0.00370 -0.0999 0.4575 0.9836
3.500 1.0437 0.00863 0.00377 -0.1035 0.4560 0.9892
3.750 1.0838 0.00872 0.00385 -0.1064 0.4541 0.9940
4.000 1.1221 0.00877 0.00389 -0.1089 0.4522 0.9963
4.250 1.1580 0.00883 0.00394 -0.1109 0.4504 0.9981
4.500 1.1929 0.00890 0.00400 -0.1127 0.4486 0.9996
4.750 1.2197 0.00897 0.00405 -0.1128 0.4468 1.0000
5.000 1.2410 0.00906 0.00412 -0.1118 0.4448 1.0000
5.250 1.2629 0.00915 0.00421 -0.1108 0.4434 1.0000
5.500 1.2857 0.00922 0.00430 -0.1101 0.4418 1.0000
5.750 1.3082 0.00929 0.00439 -0.1093 0.4399 1.0000
6.000 1.3304 0.00937 0.00448 -0.1084 0.4376 1.0000
6.250 1.3520 0.00946 0.00457 -0.1075 0.4348 1.0000
6.500 1.3724 0.00956 0.00466 -0.1063 0.4316 1.0000
6.750 1.3932 0.00967 0.00477 -0.1052 0.4290 1.0000
7.000 1.4151 0.00977 0.00489 -0.1044 0.4262 1.0000
7.250 1.4360 0.00988 0.00501 -0.1034 0.4225 1.0000
7.500 1.4551 0.01002 0.00515 -0.1020 0.4182 1.0000
7.750 1.4742 0.01017 0.00530 -0.1006 0.4139 1.0000
8.000 1.4921 0.01033 0.00546 -0.0991 0.4077 1.0000
8.250 1.5039 0.01053 0.00565 -0.0963 0.4003 1.0000
8.500 1.5152 0.01080 0.00589 -0.0935 0.3906 1.0000
8.750 1.5268 0.01112 0.00618 -0.0910 0.3813 1.0000
9.000 1.5370 0.01154 0.00656 -0.0883 0.3717 1.0000
9.250 1.5463 0.01204 0.00703 -0.0856 0.3617 1.0000
9.500 1.5578 0.01253 0.00752 -0.0834 0.3534 1.0000
9.750 1.5661 0.01319 0.00815 -0.0809 0.3450 1.0000
10.000 1.5769 0.01381 0.00877 -0.0789 0.3370 1.0000
10.250 1.5837 0.01466 0.00960 -0.0766 0.3284 1.0000
10.500 1.5938 0.01544 0.01040 -0.0748 0.3217 1.0000
10.750 1.5994 0.01653 0.01148 -0.0728 0.3143 1.0000
11.000 1.6082 0.01754 0.01251 -0.0713 0.3080 1.0000
11.250 1.6108 0.01901 0.01398 -0.0694 0.3017 1.0000
11.500 1.6186 0.02025 0.01527 -0.0682 0.2960 1.0000
11.750 1.6203 0.02200 0.01704 -0.0666 0.2901 1.0000
12.000 1.6209 0.02393 0.01900 -0.0652 0.2853 1.0000
12.250 1.6210 0.02601 0.02112 -0.0639 0.2795 1.0000
12.500 1.6098 0.02915 0.02429 -0.0623 0.2733 1.0000
12.750 1.6082 0.03161 0.02682 -0.0613 0.2692 1.0000
13.000 1.6022 0.03449 0.02974 -0.0602 0.2642 1.0000
13.250 1.5895 0.03801 0.03330 -0.0588 0.2594 1.0000
13.500 1.5839 0.04088 0.03622 -0.0578 0.2556 1.0000
13.750 1.5814 0.04344 0.03883 -0.0570 0.2520 1.0000
14.000 1.5743 0.04645 0.04186 -0.0560 0.2473 1.0000
14.250 1.5651 0.04969 0.04512 -0.0550 0.2428 1.0000
14.500 1.5673 0.05187 0.04735 -0.0544 0.2389 1.0000
14.750 1.5636 0.05465 0.05015 -0.0538 0.2340 1.0000
15.000 1.5614 0.05731 0.05281 -0.0532 0.2299 1.0000
15.250 1.5635 0.05957 0.05512 -0.0527 0.2266 1.0000
15.500 1.5672 0.06168 0.05726 -0.0524 0.2225 1.0000
15.750 1.5694 0.06395 0.05955 -0.0520 0.2186 1.0000
16.000 1.5668 0.06676 0.06237 -0.0516 0.2140 1.0000
16.250 1.5712 0.06884 0.06447 -0.0514 0.2090 1.0000
16.500 1.5745 0.07101 0.06666 -0.0511 0.2050 1.0000
16.750 1.5734 0.07370 0.06936 -0.0508 0.2005 1.0000
17.000 1.5791 0.07569 0.07139 -0.0508 0.1972 1.0000
17.250 1.5827 0.07789 0.07362 -0.0506 0.1927 1.0000
17.500 1.5808 0.08070 0.07641 -0.0504 0.1866 1.0000
17.750 1.5809 0.08332 0.07905 -0.0503 0.1800 1.0000
18.000 1.5746 0.08665 0.08234 -0.0502 0.1703 1.0000
18.250 1.5673 0.09018 0.08584 -0.0501 0.1611 1.0000
18.500 1.5613 0.09357 0.08921 -0.0501 0.1508 1.0000
18.750 1.5571 0.09675 0.09237 -0.0501 0.1417 1.0000
19.000 1.5468 0.10072 0.09631 -0.0502 0.1317 1.0000
19.250 1.5372 0.10463 0.10018 -0.0504 0.1205 1.0000
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