UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| 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: 103.92 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua2-180-il-500000.txt Download as CSV file: xf-ua2-180-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.1009 0.09090 0.08617 -0.0996 0.5403 0.0214
-9.500 0.0940 0.08674 0.08204 -0.1027 0.5398 0.0219
-9.250 0.0870 0.08233 0.07767 -0.1058 0.5392 0.0220
-9.000 0.0929 0.07956 0.07490 -0.1061 0.5382 0.0221
-8.750 0.1009 0.07744 0.07278 -0.1062 0.5371 0.0222
-8.500 0.1084 0.07541 0.07076 -0.1064 0.5363 0.0224
-8.250 0.1135 0.07302 0.06841 -0.1070 0.5358 0.0225
-8.000 0.1169 0.07050 0.06592 -0.1078 0.5353 0.0227
-7.750 0.1186 0.06786 0.06332 -0.1087 0.5348 0.0229
-7.500 0.1168 0.06490 0.06040 -0.1100 0.5342 0.0231
-7.250 0.1069 0.06154 0.05710 -0.1119 0.5334 0.0232
-7.000 0.0968 0.05845 0.05402 -0.1127 0.5327 0.0234
-6.750 0.0946 0.05505 0.05059 -0.1139 0.5319 0.0236
-6.500 0.0950 0.05169 0.04718 -0.1146 0.5312 0.0240
-6.250 0.0976 0.04822 0.04361 -0.1148 0.5304 0.0246
-6.000 0.0850 0.02778 0.02297 -0.1079 0.5292 0.0261
-5.750 0.0994 0.02597 0.02116 -0.1075 0.5283 0.0263
-5.500 0.1132 0.02418 0.01933 -0.1069 0.5274 0.0266
-5.250 0.1274 0.02240 0.01746 -0.1062 0.5266 0.0271
-5.000 0.1421 0.02049 0.01541 -0.1053 0.5258 0.0278
-4.750 0.1487 0.01711 0.01132 -0.1023 0.5251 0.0304
-4.500 0.1689 0.01559 0.00983 -0.1022 0.5242 0.0308
-4.250 0.1893 0.01449 0.00867 -0.1018 0.5232 0.0313
-4.000 0.2100 0.01346 0.00751 -0.1012 0.5221 0.0323
-3.750 0.2282 0.01209 0.00567 -0.0994 0.5211 0.0355
-3.500 0.2600 0.02490 0.01811 -0.1034 0.5208 0.0362
-3.250 0.2834 0.02431 0.01746 -0.1029 0.5194 0.0378
-2.750 0.3305 0.02247 0.01536 -0.1015 0.5182 0.0436
-2.500 0.3544 0.02172 0.01447 -0.1009 0.5176 0.0487
-2.250 0.3788 0.02122 0.01389 -0.1004 0.5168 0.0556
-2.000 0.4047 0.02078 0.01346 -0.1002 0.5159 0.0596
-1.750 0.4298 0.02052 0.01319 -0.0999 0.5149 0.0700
-1.500 0.4618 0.01804 0.01022 -0.0983 0.5138 0.0372
-1.250 0.4887 0.01757 0.00961 -0.0978 0.5125 0.0358
-1.000 0.5161 0.01753 0.00950 -0.0974 0.5112 0.0350
-0.750 0.5421 0.01689 0.00890 -0.0971 0.5099 0.0346
-0.500 0.5682 0.01649 0.00847 -0.0967 0.5083 0.0346
-0.250 0.5944 0.01616 0.00810 -0.0963 0.5068 0.0351
0.000 0.6193 0.01578 0.00773 -0.0958 0.5056 0.0357
0.250 0.6450 0.01562 0.00758 -0.0955 0.5044 0.0374
0.500 0.6710 0.01570 0.00764 -0.0953 0.5033 0.0387
0.750 0.6966 0.01574 0.00769 -0.0950 0.5024 0.0398
1.000 0.7221 0.01563 0.00759 -0.0946 0.5017 0.0410
1.250 0.7477 0.01556 0.00754 -0.0942 0.5009 0.0432
1.500 0.7735 0.01553 0.00752 -0.0939 0.4998 0.0474
2.000 0.8068 0.01407 0.00768 -0.0904 0.4974 0.6156
2.250 0.9367 0.01361 0.00805 -0.1113 0.4955 0.9928
2.500 0.9980 0.01365 0.00802 -0.1185 0.4941 1.0000
2.750 1.0200 0.01374 0.00808 -0.1176 0.4930 1.0000
3.000 1.0428 0.01378 0.00807 -0.1168 0.4916 1.0000
3.250 1.0663 0.01380 0.00805 -0.1161 0.4903 1.0000
3.500 1.0901 0.01389 0.00809 -0.1156 0.4893 1.0000
3.750 1.1141 0.01403 0.00818 -0.1151 0.4882 1.0000
4.000 1.1381 0.01429 0.00840 -0.1146 0.4869 1.0000
4.250 1.1594 0.01445 0.00858 -0.1136 0.4858 1.0000
4.500 1.1803 0.01456 0.00872 -0.1125 0.4846 1.0000
4.750 1.2009 0.01467 0.00886 -0.1114 0.4831 1.0000
5.000 1.2220 0.01475 0.00897 -0.1104 0.4814 1.0000
5.250 1.2437 0.01478 0.00901 -0.1094 0.4796 1.0000
5.500 1.2662 0.01479 0.00903 -0.1086 0.4779 1.0000
5.750 1.2897 0.01480 0.00903 -0.1080 0.4763 1.0000
6.000 1.3140 0.01478 0.00899 -0.1075 0.4748 1.0000
6.250 1.3389 0.01479 0.00898 -0.1072 0.4735 1.0000
6.500 1.3643 0.01485 0.00900 -0.1070 0.4720 1.0000
6.750 1.3849 0.01497 0.00915 -0.1059 0.4701 1.0000
7.000 1.4024 0.01505 0.00931 -0.1043 0.4679 1.0000
7.250 1.4216 0.01509 0.00940 -0.1030 0.4655 1.0000
7.500 1.4422 0.01504 0.00937 -0.1018 0.4630 1.0000
7.750 1.4639 0.01493 0.00925 -0.1009 0.4604 1.0000
8.000 1.4861 0.01484 0.00915 -0.1001 0.4582 1.0000
8.250 1.5100 0.01489 0.00917 -0.0997 0.4559 1.0000
8.500 1.5222 0.01502 0.00941 -0.0971 0.4531 1.0000
8.750 1.5371 0.01512 0.00958 -0.0951 0.4501 1.0000
9.000 1.5530 0.01517 0.00967 -0.0932 0.4471 1.0000
9.250 1.5666 0.01520 0.00971 -0.0908 0.4443 1.0000
9.500 1.5837 0.01524 0.00972 -0.0892 0.4415 1.0000
9.750 1.5898 0.01550 0.01008 -0.0857 0.4378 1.0000
10.000 1.5988 0.01571 0.01037 -0.0829 0.4329 1.0000
10.250 1.6121 0.01591 0.01057 -0.0810 0.4289 1.0000
10.500 1.6228 0.01626 0.01097 -0.0788 0.4239 1.0000
10.750 1.6316 0.01672 0.01149 -0.0765 0.4171 1.0000
11.000 1.6404 0.01725 0.01202 -0.0743 0.4107 1.0000
11.250 1.6471 0.01800 0.01283 -0.0722 0.4022 1.0000
11.500 1.6513 0.01896 0.01380 -0.0699 0.3925 1.0000
11.750 1.6508 0.02031 0.01514 -0.0675 0.3816 1.0000
12.250 1.6365 0.02446 0.01926 -0.0625 0.3589 1.0000
12.500 1.6222 0.02732 0.02211 -0.0600 0.3487 1.0000
12.750 1.6053 0.03057 0.02532 -0.0577 0.3399 1.0000
13.000 1.5958 0.03354 0.02833 -0.0562 0.3322 1.0000
13.250 1.5821 0.03680 0.03155 -0.0545 0.3242 1.0000
13.500 1.5762 0.03965 0.03448 -0.0535 0.3176 1.0000
13.750 1.5663 0.04273 0.03752 -0.0522 0.3100 1.0000
14.000 1.5630 0.04547 0.04034 -0.0515 0.3039 1.0000
14.250 1.5583 0.04824 0.04314 -0.0507 0.2972 1.0000
14.500 1.5551 0.05090 0.04581 -0.0500 0.2911 1.0000
14.750 1.5527 0.05359 0.04855 -0.0494 0.2849 1.0000
15.000 1.5511 0.05610 0.05104 -0.0488 0.2792 1.0000
15.250 1.5505 0.05865 0.05364 -0.0483 0.2733 1.0000
15.500 1.5491 0.06125 0.05624 -0.0479 0.2675 1.0000
15.750 1.5512 0.06345 0.05844 -0.0475 0.2628 1.0000
16.000 1.5527 0.06582 0.06086 -0.0472 0.2579 1.0000
16.250 1.5514 0.06841 0.06341 -0.0468 0.2521 1.0000
16.500 1.5555 0.07043 0.06545 -0.0465 0.2478 1.0000
16.750 1.5616 0.07232 0.06740 -0.0463 0.2446 1.0000
17.000 1.5642 0.07457 0.06967 -0.0461 0.2404 1.0000
17.250 1.5682 0.07658 0.07165 -0.0459 0.2359 1.0000
17.500 1.5738 0.07852 0.07365 -0.0458 0.2326 1.0000
17.750 1.5778 0.08069 0.07591 -0.0458 0.2292 1.0000
18.000 1.5792 0.08312 0.07836 -0.0457 0.2248 1.0000
18.250 1.5831 0.08515 0.08036 -0.0456 0.2200 1.0000
18.500 1.5850 0.08769 0.08302 -0.0457 0.2167 1.0000
18.750 1.5872 0.09016 0.08557 -0.0458 0.2127 1.0000
19.000 1.5886 0.09264 0.08810 -0.0460 0.2089 1.0000
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Polar data table (+)
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