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UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
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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