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UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: UA(2)-180 (University of Alberta/Marsden) (ua2-180-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.55 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ua2-180-il-1000000-n5.txt
Download as CSV file: xf-ua2-180-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0864   0.09120   0.08707  -0.1000   0.4985   0.0098
 -10.000   0.0896   0.08808   0.08396  -0.1011   0.4982   0.0098
  -9.750   0.0932   0.08511   0.08102  -0.1022   0.4976   0.0096
  -9.500   0.0982   0.08249   0.07841  -0.1032   0.4971   0.0101
  -9.250   0.0994   0.07927   0.07521  -0.1043   0.4966   0.0098
  -9.000   0.1000   0.07603   0.07200  -0.1054   0.4961   0.0098
  -8.750   0.0996   0.07276   0.06875  -0.1066   0.4955   0.0099
  -8.500   0.0972   0.06930   0.06533  -0.1078   0.4951   0.0097
  -8.250   0.0919   0.06557   0.06163  -0.1092   0.4945   0.0096
  -8.000   0.0838   0.06169   0.05779  -0.1109   0.4940   0.0097
  -7.750   0.0636   0.05713   0.05329  -0.1136   0.4936   0.0096
  -7.500   0.0433   0.05279   0.04893  -0.1144   0.4931   0.0097
  -7.250   0.0271   0.04716   0.04322  -0.1152   0.4926   0.0096
  -7.000   0.0219   0.04270   0.03864  -0.1148   0.4921   0.0098
  -6.750   0.0172   0.03782   0.03356  -0.1133   0.4916   0.0101
  -6.500   0.0126   0.03255   0.02799  -0.1108   0.4910   0.0102
  -6.250  -0.0244   0.02045   0.01472  -0.1025   0.4909   0.0111
  -6.000  -0.0032   0.01957   0.01370  -0.1016   0.4899   0.0112
  -5.750   0.0197   0.01892   0.01293  -0.1009   0.4889   0.0113
  -5.500   0.0438   0.01851   0.01243  -0.1003   0.4877   0.0115
  -5.250   0.0666   0.01772   0.01150  -0.0995   0.4864   0.0116
  -5.000   0.0907   0.01710   0.01079  -0.0989   0.4853   0.0117
  -4.750   0.1154   0.01649   0.01008  -0.0984   0.4846   0.0120
  -4.500   0.1400   0.01574   0.00922  -0.0978   0.4839   0.0123
  -4.250   0.1644   0.01484   0.00819  -0.0971   0.4831   0.0126
  -4.000   0.1889   0.01397   0.00720  -0.0964   0.4820   0.0130
  -3.750   0.2140   0.01334   0.00647  -0.0958   0.4810   0.0133
  -3.500   0.2398   0.01291   0.00597  -0.0954   0.4796   0.0136
  -3.250   0.2651   0.01247   0.00548  -0.0949   0.4784   0.0138
  -3.000   0.2916   0.01224   0.00524  -0.0947   0.4771   0.0141
  -2.750   0.3183   0.01208   0.00506  -0.0944   0.4761   0.0143
  -2.500   0.3453   0.01198   0.00495  -0.0943   0.4752   0.0147
  -2.250   0.3720   0.01183   0.00478  -0.0941   0.4743   0.0151
  -2.000   0.3980   0.01160   0.00452  -0.0937   0.4734   0.0155
  -1.750   0.4238   0.01139   0.00427  -0.0933   0.4724   0.0159
  -1.500   0.4498   0.01122   0.00407  -0.0929   0.4712   0.0163
  -1.250   0.4761   0.01107   0.00389  -0.0926   0.4700   0.0166
  -1.000   0.5022   0.01086   0.00369  -0.0923   0.4692   0.0170
  -0.750   0.5289   0.01074   0.00358  -0.0921   0.4683   0.0175
  -0.500   0.5558   0.01065   0.00350  -0.0919   0.4674   0.0180
  -0.250   0.5828   0.01057   0.00342  -0.0918   0.4665   0.0186
   0.000   0.6098   0.01051   0.00336  -0.0917   0.4656   0.0196
   0.250   0.6367   0.01044   0.00328  -0.0915   0.4646   0.0201
   0.500   0.6631   0.01033   0.00318  -0.0913   0.4634   0.0207
   0.750   0.6898   0.01026   0.00311  -0.0911   0.4621   0.0214
   1.000   0.7165   0.01021   0.00306  -0.0910   0.4606   0.0222
   1.250   0.7431   0.01018   0.00302  -0.0908   0.4590   0.0233
   1.500   0.7694   0.01015   0.00298  -0.0906   0.4574   0.0246
   1.750   0.7954   0.01013   0.00295  -0.0903   0.4558   0.0257
   2.000   0.8221   0.01011   0.00295  -0.0902   0.4545   0.0272
   2.250   0.8491   0.01010   0.00295  -0.0902   0.4533   0.0284
   2.500   0.8758   0.01009   0.00295  -0.0901   0.4519   0.0311
   2.750   0.9025   0.01009   0.00297  -0.0900   0.4504   0.0350
   3.000   0.9229   0.00958   0.00305  -0.0889   0.4489   0.3061
   3.250   0.9363   0.00883   0.00317  -0.0864   0.4476   0.6453
   3.500   1.0028   0.00832   0.00348  -0.0949   0.4457   0.9631
   3.750   1.0506   0.00846   0.00359  -0.0994   0.4437   0.9782
   4.000   1.0891   0.00860   0.00369  -0.1019   0.4418   0.9873
   4.250   1.1317   0.00875   0.00381  -0.1054   0.4395   0.9946
   5.000   1.2393   0.00900   0.00404  -0.1115   0.4306   1.0000
   5.250   1.2594   0.00912   0.00412  -0.1102   0.4261   1.0000
   5.500   1.2806   0.00922   0.00422  -0.1092   0.4222   1.0000
   5.750   1.3014   0.00934   0.00432  -0.1080   0.4159   1.0000
   6.000   1.3210   0.00948   0.00444  -0.1067   0.4112   1.0000
   6.250   1.3411   0.00961   0.00457  -0.1055   0.4066   1.0000
   6.500   1.3602   0.00978   0.00471  -0.1041   0.3990   1.0000
   6.750   1.3772   0.00999   0.00489  -0.1023   0.3901   1.0000
   7.000   1.3895   0.01035   0.00517  -0.0997   0.3740   1.0000
   7.250   1.3935   0.01081   0.00554  -0.0955   0.3569   1.0000
   7.500   1.3974   0.01123   0.00590  -0.0913   0.3463   1.0000
   7.750   1.4036   0.01168   0.00631  -0.0877   0.3373   1.0000
   8.000   1.4149   0.01206   0.00667  -0.0851   0.3316   1.0000
   8.250   1.4262   0.01248   0.00709  -0.0827   0.3257   1.0000
   8.500   1.4329   0.01311   0.00769  -0.0797   0.3179   1.0000
   8.750   1.4491   0.01346   0.00806  -0.0783   0.3149   1.0000
   9.000   1.4640   0.01389   0.00852  -0.0768   0.3111   1.0000
   9.250   1.4759   0.01447   0.00911  -0.0750   0.3065   1.0000
   9.500   1.4848   0.01524   0.00988  -0.0729   0.3011   1.0000
   9.750   1.4970   0.01593   0.01058  -0.0714   0.2939   1.0000
  10.000   1.5044   0.01692   0.01157  -0.0696   0.2869   1.0000
  10.250   1.5080   0.01824   0.01288  -0.0676   0.2747   1.0000
  10.500   1.5066   0.02002   0.01463  -0.0654   0.2635   1.0000
  10.750   1.4951   0.02270   0.01728  -0.0628   0.2505   1.0000
  11.000   1.4836   0.02561   0.02019  -0.0607   0.2418   1.0000
  11.250   1.4803   0.02811   0.02272  -0.0594   0.2371   1.0000
  11.500   1.4795   0.03054   0.02521  -0.0584   0.2345   1.0000
  11.750   1.4708   0.03370   0.02841  -0.0572   0.2304   1.0000
  12.000   1.4699   0.03614   0.03091  -0.0563   0.2289   1.0000
  12.250   1.4650   0.03896   0.03378  -0.0552   0.2261   1.0000
  12.500   1.4654   0.04131   0.03618  -0.0545   0.2241   1.0000
  12.750   1.4690   0.04337   0.03829  -0.0538   0.2233   1.0000
  13.000   1.4700   0.04562   0.04059  -0.0531   0.2198   1.0000
  13.250   1.4709   0.04792   0.04294  -0.0525   0.2179   1.0000
  13.500   1.4712   0.05025   0.04529  -0.0518   0.2149   1.0000
  13.750   1.4679   0.05298   0.04805  -0.0510   0.2114   1.0000
  14.000   1.4698   0.05522   0.05031  -0.0505   0.2083   1.0000
  14.250   1.4792   0.05677   0.05191  -0.0502   0.2068   1.0000
  14.500   1.4835   0.05883   0.05400  -0.0499   0.2022   1.0000
  14.750   1.4867   0.06100   0.05619  -0.0495   0.1983   1.0000
  15.000   1.4878   0.06338   0.05856  -0.0490   0.1934   1.0000
  15.250   1.4941   0.06527   0.06048  -0.0488   0.1882   1.0000
  15.500   1.4856   0.06873   0.06389  -0.0483   0.1755   1.0000
  15.750   1.4760   0.07228   0.06735  -0.0477   0.1610   1.0000
  16.000   1.4717   0.07538   0.07043  -0.0473   0.1542   1.0000
  16.250   1.4717   0.07801   0.07306  -0.0471   0.1478   1.0000
  16.500   1.4708   0.08075   0.07579  -0.0469   0.1419   1.0000
  16.750   1.4735   0.08316   0.07823  -0.0468   0.1387   1.0000
  17.000   1.4764   0.08551   0.08061  -0.0468   0.1341   1.0000
  17.250   1.4733   0.08854   0.08362  -0.0466   0.1267   1.0000
  17.500   1.4689   0.09179   0.08685  -0.0466   0.1162   1.0000
  17.750   1.4448   0.09739   0.09228  -0.0464   0.0911   1.0000
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