UA(2)-180 smoothed (ua2-180sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: UA(2)-180 smoothed (ua2-180sm-il) Reynolds number: 500,000 Max Cl/Cd: 106.82 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ua2-180sm-il-500000-n5.txt Download as CSV file: xf-ua2-180sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0717 0.08944 0.08460 -0.0974 0.5118 0.0132
-9.750 0.0746 0.08636 0.08153 -0.0985 0.5113 0.0131
-9.500 0.0752 0.08293 0.07812 -0.0998 0.5107 0.0133
-9.250 0.0752 0.07949 0.07470 -0.1011 0.5102 0.0135
-9.000 0.0615 0.07357 0.06882 -0.1037 0.5099 0.0142
-8.750 0.0779 0.07359 0.06884 -0.1034 0.5090 0.0148
-8.500 0.0721 0.06949 0.06477 -0.1051 0.5085 0.0146
-8.250 0.0621 0.06491 0.06023 -0.1072 0.5080 0.0145
-8.000 -0.0065 0.05216 0.04752 -0.1138 0.5081 0.0141
-7.750 -0.0192 0.04762 0.04287 -0.1140 0.5076 0.0142
-7.500 -0.0307 0.04275 0.03783 -0.1132 0.5071 0.0142
-7.250 -0.0252 0.04064 0.03560 -0.1122 0.5063 0.0143
-7.000 -0.0162 0.03884 0.03367 -0.1112 0.5055 0.0145
-6.750 -0.0125 0.03555 0.03017 -0.1096 0.5051 0.0146
-6.500 -0.0007 0.03356 0.02802 -0.1084 0.5047 0.0148
-6.250 0.0110 0.03126 0.02552 -0.1069 0.5042 0.0151
-6.000 0.0245 0.02909 0.02311 -0.1054 0.5037 0.0154
-5.750 0.0374 0.02653 0.02023 -0.1034 0.5031 0.0161
-5.500 0.0520 0.02411 0.01742 -0.1015 0.5026 0.0163
-5.250 0.0705 0.02236 0.01534 -0.1000 0.5020 0.0166
-5.000 0.0914 0.02102 0.01369 -0.0987 0.5013 0.0169
-4.750 0.1140 0.02000 0.01242 -0.0978 0.5005 0.0172
-4.500 0.1378 0.01915 0.01149 -0.0972 0.4996 0.0174
-4.250 0.1627 0.01857 0.01085 -0.0968 0.4988 0.0177
-4.000 0.1881 0.01817 0.01040 -0.0965 0.4979 0.0181
-3.750 0.2137 0.01771 0.00988 -0.0961 0.4972 0.0185
-3.500 0.2394 0.01715 0.00921 -0.0957 0.4965 0.0188
-3.250 0.2652 0.01663 0.00860 -0.0953 0.4958 0.0192
-3.000 0.2913 0.01618 0.00806 -0.0949 0.4951 0.0195
-2.750 0.3174 0.01578 0.00759 -0.0945 0.4944 0.0197
-2.500 0.3436 0.01546 0.00720 -0.0942 0.4937 0.0201
-2.250 0.3699 0.01520 0.00688 -0.0939 0.4931 0.0204
-2.000 0.3955 0.01484 0.00650 -0.0935 0.4924 0.0207
-1.750 0.4209 0.01453 0.00620 -0.0931 0.4917 0.0212
-1.500 0.4468 0.01435 0.00601 -0.0928 0.4911 0.0218
-1.250 0.4729 0.01419 0.00583 -0.0925 0.4903 0.0224
-1.000 0.4990 0.01406 0.00568 -0.0922 0.4894 0.0230
-0.750 0.5251 0.01394 0.00554 -0.0919 0.4886 0.0234
-0.500 0.5511 0.01380 0.00541 -0.0916 0.4880 0.0239
-0.250 0.5772 0.01370 0.00531 -0.0913 0.4874 0.0244
0.000 0.6030 0.01355 0.00518 -0.0910 0.4868 0.0251
0.250 0.6292 0.01348 0.00512 -0.0908 0.4862 0.0258
0.500 0.6557 0.01343 0.00509 -0.0906 0.4855 0.0271
0.750 0.6822 0.01341 0.00506 -0.0904 0.4846 0.0284
1.000 0.7085 0.01338 0.00503 -0.0902 0.4836 0.0297
1.250 0.7350 0.01337 0.00503 -0.0901 0.4827 0.0316
1.500 0.7615 0.01336 0.00503 -0.0899 0.4817 0.0354
1.750 0.7774 0.01239 0.00508 -0.0882 0.4805 0.4101
2.000 0.7862 0.01147 0.00516 -0.0846 0.4793 0.7384
2.500 0.9296 0.01145 0.00554 -0.1029 0.4764 0.9849
2.750 0.9776 0.01157 0.00560 -0.1074 0.4752 0.9936
3.000 1.0286 0.01168 0.00562 -0.1125 0.4738 0.9992
3.250 1.0560 0.01178 0.00570 -0.1128 0.4725 1.0000
3.500 1.0771 0.01184 0.00579 -0.1117 0.4711 1.0000
3.750 1.0985 0.01192 0.00587 -0.1106 0.4695 1.0000
4.000 1.1199 0.01198 0.00594 -0.1096 0.4677 1.0000
4.250 1.1416 0.01204 0.00601 -0.1086 0.4658 1.0000
4.500 1.1633 0.01210 0.00606 -0.1076 0.4640 1.0000
4.750 1.1851 0.01216 0.00610 -0.1067 0.4623 1.0000
5.000 1.2071 0.01223 0.00615 -0.1058 0.4607 1.0000
5.250 1.2291 0.01231 0.00621 -0.1049 0.4591 1.0000
5.500 1.2509 0.01242 0.00632 -0.1040 0.4576 1.0000
5.750 1.2719 0.01254 0.00648 -0.1029 0.4558 1.0000
6.000 1.2928 0.01265 0.00663 -0.1019 0.4537 1.0000
6.250 1.3136 0.01274 0.00676 -0.1008 0.4514 1.0000
6.500 1.3343 0.01284 0.00687 -0.0997 0.4492 1.0000
6.750 1.3549 0.01293 0.00697 -0.0987 0.4472 1.0000
7.000 1.3751 0.01303 0.00707 -0.0975 0.4453 1.0000
7.250 1.3949 0.01315 0.00720 -0.0963 0.4432 1.0000
7.500 1.4141 0.01330 0.00741 -0.0950 0.4402 1.0000
7.750 1.4327 0.01344 0.00760 -0.0937 0.4371 1.0000
8.000 1.4485 0.01356 0.00774 -0.0917 0.4337 1.0000
8.250 1.4620 0.01369 0.00787 -0.0893 0.4308 1.0000
8.500 1.4772 0.01388 0.00810 -0.0874 0.4276 1.0000
8.750 1.4923 0.01408 0.00836 -0.0855 0.4234 1.0000
9.000 1.5060 0.01430 0.00860 -0.0834 0.4189 1.0000
9.250 1.5197 0.01458 0.00889 -0.0815 0.4141 1.0000
9.500 1.5334 0.01491 0.00926 -0.0796 0.4077 1.0000
9.750 1.5438 0.01535 0.00970 -0.0774 0.4006 1.0000
10.000 1.5540 0.01588 0.01025 -0.0753 0.3923 1.0000
10.250 1.5617 0.01659 0.01095 -0.0731 0.3839 1.0000
10.500 1.5648 0.01758 0.01192 -0.0705 0.3749 1.0000
10.750 1.5694 0.01867 0.01302 -0.0684 0.3657 1.0000
11.000 1.5698 0.02011 0.01446 -0.0661 0.3574 1.0000
11.250 1.5676 0.02189 0.01624 -0.0639 0.3486 1.0000
11.500 1.5649 0.02385 0.01822 -0.0620 0.3402 1.0000
11.750 1.5535 0.02661 0.02098 -0.0598 0.3313 1.0000
12.000 1.5504 0.02894 0.02336 -0.0584 0.3240 1.0000
12.250 1.5361 0.03232 0.02675 -0.0567 0.3165 1.0000
12.500 1.5322 0.03493 0.02942 -0.0556 0.3099 1.0000
12.750 1.5189 0.03842 0.03292 -0.0542 0.3029 1.0000
13.000 1.5152 0.04108 0.03563 -0.0533 0.2973 1.0000
13.250 1.5085 0.04404 0.03861 -0.0523 0.2911 1.0000
13.500 1.5018 0.04700 0.04158 -0.0514 0.2855 1.0000
13.750 1.5019 0.04936 0.04399 -0.0507 0.2800 1.0000
14.000 1.4960 0.05231 0.04694 -0.0499 0.2741 1.0000
14.250 1.4988 0.05445 0.04910 -0.0494 0.2699 1.0000
14.500 1.5011 0.05668 0.05138 -0.0489 0.2656 1.0000
14.750 1.5025 0.05897 0.05369 -0.0485 0.2613 1.0000
15.000 1.5051 0.06114 0.05586 -0.0480 0.2573 1.0000
15.250 1.5104 0.06312 0.05791 -0.0478 0.2536 1.0000
15.500 1.5136 0.06532 0.06015 -0.0475 0.2492 1.0000
15.750 1.5179 0.06736 0.06220 -0.0472 0.2457 1.0000
16.000 1.5234 0.06927 0.06414 -0.0470 0.2425 1.0000
16.250 1.5297 0.07119 0.06612 -0.0468 0.2395 1.0000
16.500 1.5347 0.07322 0.06821 -0.0467 0.2360 1.0000
16.750 1.5359 0.07567 0.07065 -0.0465 0.2308 1.0000
17.000 1.5383 0.07802 0.07304 -0.0464 0.2258 1.0000
17.250 1.5413 0.08032 0.07540 -0.0463 0.2217 1.0000
17.500 1.5399 0.08309 0.07815 -0.0462 0.2159 1.0000
17.750 1.5470 0.08491 0.08003 -0.0462 0.2135 1.0000
18.000 1.5513 0.08711 0.08230 -0.0462 0.2099 1.0000
18.250 1.5480 0.09021 0.08540 -0.0462 0.2033 1.0000
18.500 1.5500 0.09265 0.08788 -0.0463 0.1988 1.0000
18.750 1.5520 0.09512 0.09042 -0.0465 0.1945 1.0000
19.000 1.5475 0.09838 0.09367 -0.0466 0.1882 1.0000
19.250 1.5462 0.10131 0.09665 -0.0468 0.1810 1.0000
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Polar data table (+)
Polar graphs
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