UA(2)-180 smoothed (ua2-180sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: UA(2)-180 smoothed (ua2-180sm-il) Reynolds number: 500,000 Max Cl/Cd: 102.9 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua2-180sm-il-500000.txt Download as CSV file: xf-ua2-180sm-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0953 0.09735 0.09297 -0.0861 0.5431 0.0211
-10.750 0.0882 0.09283 0.08847 -0.0889 0.5427 0.0213
-10.500 0.0895 0.08887 0.08451 -0.0903 0.5421 0.0214
-10.250 0.0988 0.08615 0.08179 -0.0905 0.5413 0.0216
-10.000 0.1096 0.08390 0.07952 -0.0906 0.5405 0.0218
-9.750 0.1180 0.08145 0.07707 -0.0910 0.5396 0.0221
-9.500 0.1229 0.07858 0.07419 -0.0919 0.5389 0.0224
-9.250 0.1274 0.07571 0.07133 -0.0928 0.5380 0.0228
-9.000 0.1304 0.07267 0.06829 -0.0938 0.5372 0.0232
-8.750 0.1317 0.06928 0.06493 -0.0950 0.5368 0.0240
-8.500 0.1115 0.06254 0.05823 -0.0998 0.5367 0.0252
-8.250 0.0992 0.05685 0.05258 -0.1036 0.5365 0.0253
-8.000 0.1016 0.05393 0.04970 -0.1031 0.5360 0.0256
-7.750 0.1016 0.05090 0.04670 -0.1042 0.5355 0.0257
-7.500 0.0231 0.05377 0.04907 -0.1162 0.5361 0.0253
-7.250 0.0350 0.05163 0.04705 -0.1157 0.5355 0.0256
-7.000 0.0428 0.04999 0.04541 -0.1151 0.5349 0.0258
-6.750 0.0499 0.04806 0.04345 -0.1145 0.5342 0.0260
-6.500 0.0587 0.04621 0.04155 -0.1139 0.5334 0.0264
-6.250 0.0672 0.04391 0.03917 -0.1132 0.5325 0.0269
-6.000 0.0611 0.03940 0.03397 -0.1102 0.5319 0.0298
-5.750 0.0711 0.03586 0.03038 -0.1094 0.5311 0.0303
-5.500 0.0895 0.03445 0.02898 -0.1089 0.5302 0.0307
-5.250 0.1076 0.03314 0.02762 -0.1083 0.5294 0.0313
-5.000 0.1259 0.03177 0.02612 -0.1074 0.5286 0.0324
-4.750 0.1380 0.02927 0.02312 -0.1049 0.5279 0.0358
-4.500 0.1597 0.02807 0.02192 -0.1045 0.5271 0.0365
-4.250 0.1821 0.02724 0.02103 -0.1040 0.5263 0.0383
-4.000 0.2011 0.02581 0.01926 -0.1026 0.5255 0.0424
-3.750 0.2247 0.02495 0.01839 -0.1022 0.5248 0.0440
-3.500 0.2464 0.02409 0.01721 -0.1011 0.5240 0.0494
-3.250 0.2710 0.02320 0.01633 -0.1009 0.5232 0.0514
-3.000 0.2944 0.02263 0.01554 -0.1001 0.5224 0.0582
-2.750 0.3199 0.02198 0.01491 -0.1000 0.5214 0.0614
-2.500 0.3490 0.01934 0.01142 -0.0975 0.5201 0.0353
-2.250 0.3760 0.01850 0.01059 -0.0972 0.5195 0.0346
-2.000 0.4024 0.01764 0.00973 -0.0969 0.5190 0.0337
-1.750 0.4286 0.01711 0.00918 -0.0965 0.5183 0.0334
-1.500 0.4545 0.01673 0.00879 -0.0960 0.5176 0.0334
-1.250 0.4800 0.01643 0.00849 -0.0956 0.5169 0.0336
-1.000 0.5055 0.01621 0.00826 -0.0951 0.5161 0.0339
-0.750 0.5312 0.01606 0.00812 -0.0947 0.5151 0.0347
-0.500 0.5560 0.01583 0.00789 -0.0942 0.5140 0.0356
-0.250 0.5808 0.01562 0.00770 -0.0937 0.5130 0.0365
0.000 0.6064 0.01554 0.00763 -0.0933 0.5121 0.0375
0.250 0.6324 0.01549 0.00757 -0.0930 0.5111 0.0389
0.500 0.6588 0.01545 0.00752 -0.0928 0.5100 0.0405
0.750 0.6853 0.01539 0.00745 -0.0926 0.5089 0.0441
1.000 0.7121 0.01536 0.00743 -0.0924 0.5078 0.0545
1.250 0.7226 0.01400 0.00750 -0.0898 0.5068 0.5507
1.500 0.8208 0.01343 0.00796 -0.1038 0.5053 0.9779
1.750 0.8928 0.01397 0.00837 -0.1132 0.5034 0.9932
2.000 0.9535 0.01394 0.00830 -0.1202 0.5024 1.0000
2.250 0.9742 0.01402 0.00838 -0.1191 0.5013 1.0000
2.500 0.9952 0.01411 0.00847 -0.1181 0.4999 1.0000
2.750 1.0164 0.01421 0.00856 -0.1170 0.4985 1.0000
3.000 1.0379 0.01429 0.00864 -0.1160 0.4969 1.0000
3.250 1.0597 0.01438 0.00870 -0.1151 0.4954 1.0000
3.500 1.0821 0.01442 0.00873 -0.1143 0.4938 1.0000
3.750 1.1054 0.01445 0.00872 -0.1136 0.4923 1.0000
4.000 1.1296 0.01448 0.00870 -0.1131 0.4908 1.0000
4.250 1.1547 0.01455 0.00871 -0.1127 0.4893 1.0000
4.500 1.1794 0.01489 0.00899 -0.1125 0.4874 1.0000
4.750 1.1995 0.01491 0.00906 -0.1112 0.4860 1.0000
5.000 1.2200 0.01499 0.00917 -0.1100 0.4844 1.0000
5.250 1.2405 0.01505 0.00928 -0.1089 0.4824 1.0000
5.500 1.2620 0.01514 0.00938 -0.1079 0.4807 1.0000
5.750 1.2842 0.01519 0.00945 -0.1071 0.4790 1.0000
6.000 1.3078 0.01519 0.00944 -0.1065 0.4772 1.0000
6.250 1.3326 0.01517 0.00939 -0.1061 0.4756 1.0000
6.500 1.3583 0.01518 0.00937 -0.1060 0.4741 1.0000
6.750 1.3846 0.01531 0.00946 -0.1060 0.4725 1.0000
7.000 1.4037 0.01546 0.00967 -0.1047 0.4707 1.0000
7.250 1.4208 0.01553 0.00982 -0.1030 0.4684 1.0000
7.500 1.4398 0.01557 0.00992 -0.1016 0.4660 1.0000
7.750 1.4609 0.01556 0.00993 -0.1007 0.4636 1.0000
8.000 1.4836 0.01550 0.00988 -0.1000 0.4615 1.0000
8.250 1.5075 0.01546 0.00982 -0.0995 0.4596 1.0000
8.500 1.5321 0.01548 0.00982 -0.0992 0.4575 1.0000
8.750 1.5460 0.01562 0.01005 -0.0970 0.4549 1.0000
9.000 1.5595 0.01570 0.01021 -0.0947 0.4517 1.0000
9.250 1.5758 0.01571 0.01026 -0.0929 0.4486 1.0000
9.500 1.5925 0.01567 0.01024 -0.0912 0.4458 1.0000
9.750 1.6104 0.01565 0.01019 -0.0896 0.4430 1.0000
10.000 1.6128 0.01589 0.01055 -0.0854 0.4392 1.0000
10.250 1.6215 0.01608 0.01081 -0.0826 0.4349 1.0000
10.500 1.6344 0.01623 0.01098 -0.0805 0.4310 1.0000
10.750 1.6459 0.01652 0.01130 -0.0784 0.4267 1.0000
11.000 1.6537 0.01700 0.01187 -0.0760 0.4207 1.0000
11.250 1.6642 0.01740 0.01227 -0.0740 0.4152 1.0000
11.500 1.6706 0.01815 0.01310 -0.0718 0.4075 1.0000
11.750 1.6760 0.01900 0.01394 -0.0697 0.4001 1.0000
12.000 1.6787 0.02017 0.01516 -0.0676 0.3908 1.0000
12.250 1.6786 0.02165 0.01665 -0.0655 0.3816 1.0000
12.500 1.6733 0.02360 0.01857 -0.0632 0.3721 1.0000
12.750 1.6657 0.02592 0.02090 -0.0611 0.3622 1.0000
13.000 1.6557 0.02858 0.02357 -0.0591 0.3529 1.0000
13.250 1.6419 0.03164 0.02660 -0.0571 0.3436 1.0000
13.500 1.6292 0.03489 0.02989 -0.0555 0.3344 1.0000
13.750 1.6188 0.03799 0.03299 -0.0542 0.3266 1.0000
14.000 1.6104 0.04099 0.03601 -0.0530 0.3192 1.0000
14.250 1.6047 0.04375 0.03877 -0.0520 0.3126 1.0000
14.500 1.6006 0.04646 0.04152 -0.0512 0.3063 1.0000
14.750 1.6005 0.04862 0.04362 -0.0503 0.3004 1.0000
15.000 1.5967 0.05144 0.04654 -0.0498 0.2949 1.0000
15.250 1.5971 0.05373 0.04882 -0.0492 0.2894 1.0000
15.500 1.6021 0.05549 0.05056 -0.0486 0.2848 1.0000
15.750 1.6014 0.05805 0.05322 -0.0482 0.2802 1.0000
16.000 1.6050 0.06008 0.05526 -0.0478 0.2756 1.0000
16.250 1.6155 0.06123 0.05636 -0.0474 0.2714 1.0000
16.500 1.6106 0.06436 0.05961 -0.0472 0.2666 1.0000
16.750 1.6133 0.06655 0.06183 -0.0469 0.2622 1.0000
17.000 1.6180 0.06840 0.06363 -0.0466 0.2563 1.0000
17.250 1.6149 0.07140 0.06674 -0.0465 0.2521 1.0000
17.500 1.6168 0.07375 0.06913 -0.0463 0.2475 1.0000
17.750 1.6245 0.07529 0.07063 -0.0461 0.2431 1.0000
18.000 1.6223 0.07821 0.07365 -0.0461 0.2390 1.0000
18.250 1.6225 0.08080 0.07632 -0.0461 0.2345 1.0000
18.500 1.6249 0.08304 0.07850 -0.0460 0.2289 1.0000
18.750 1.6162 0.08686 0.08244 -0.0461 0.2229 1.0000
19.000 1.6161 0.08952 0.08512 -0.0462 0.2177 1.0000
19.250 1.6154 0.09220 0.08781 -0.0463 0.2129 1.0000
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