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UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: UA(2)-180 (University of Alberta/Marsden) (ua2-180-il)
Reynolds number: 500,000
Max Cl/Cd: 106.99 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ua2-180-il-500000-n5.txt
Download as CSV file: xf-ua2-180-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0769   0.09867   0.09373  -0.0946   0.5138   0.0162
 -10.250   0.0744   0.09477   0.08985  -0.0969   0.5133   0.0166
 -10.000   0.0754   0.09118   0.08629  -0.0985   0.5128   0.0166
  -9.750   0.0807   0.08840   0.08353  -0.0996   0.5122   0.0166
  -9.500   0.0845   0.08536   0.08051  -0.1007   0.5116   0.0166
  -9.250   0.0876   0.08230   0.07746  -0.1019   0.5110   0.0167
  -9.000   0.0891   0.07898   0.07417  -0.1032   0.5104   0.0167
  -8.750   0.0898   0.07559   0.07081  -0.1046   0.5098   0.0167
  -8.500   0.0915   0.07255   0.06780  -0.1057   0.5092   0.0167
  -8.250   0.0923   0.06946   0.06474  -0.1069   0.5085   0.0166
  -7.250   0.0528   0.05402   0.04936  -0.1122   0.5064   0.0134
  -7.000   0.0447   0.04937   0.04461  -0.1129   0.5059   0.0134
  -6.750   0.0383   0.04438   0.03945  -0.1125   0.5053   0.0135
  -6.500   0.0411   0.04102   0.03593  -0.1115   0.5048   0.0134
  -6.250   0.0449   0.03749   0.03218  -0.1101   0.5041   0.0134
  -6.000   0.0441   0.03223   0.02647  -0.1073   0.5036   0.0137
  -5.750   0.0578   0.03052   0.02459  -0.1060   0.5029   0.0139
  -5.500   0.0759   0.02943   0.02339  -0.1052   0.5021   0.0140
  -5.250   0.0961   0.02866   0.02251  -0.1045   0.5013   0.0142
  -5.000   0.1144   0.02716   0.02084  -0.1034   0.5007   0.0144
  -4.750   0.1318   0.02518   0.01861  -0.1018   0.5002   0.0145
  -4.500   0.1515   0.02361   0.01681  -0.1006   0.4996   0.0147
  -4.250   0.1727   0.02224   0.01521  -0.0994   0.4989   0.0149
  -4.000   0.1951   0.02102   0.01379  -0.0984   0.4982   0.0151
  -3.750   0.2184   0.01993   0.01250  -0.0975   0.4971   0.0155
  -3.500   0.2426   0.01893   0.01131  -0.0967   0.4958   0.0159
  -3.250   0.2676   0.01804   0.01025  -0.0961   0.4945   0.0162
  -3.000   0.2931   0.01731   0.00931  -0.0954   0.4931   0.0168
  -2.750   0.3187   0.01677   0.00874  -0.0951   0.4919   0.0171
  -2.500   0.3448   0.01648   0.00842  -0.0949   0.4910   0.0175
  -2.250   0.3710   0.01608   0.00798  -0.0945   0.4901   0.0180
  -2.000   0.3971   0.01566   0.00750  -0.0942   0.4892   0.0183
  -1.750   0.4230   0.01527   0.00705  -0.0938   0.4881   0.0188
  -1.500   0.4490   0.01493   0.00665  -0.0934   0.4870   0.0194
  -1.250   0.4750   0.01468   0.00632  -0.0930   0.4860   0.0199
  -1.000   0.5006   0.01440   0.00604  -0.0926   0.4850   0.0203
  -0.750   0.5259   0.01414   0.00582  -0.0922   0.4843   0.0210
  -0.500   0.5519   0.01400   0.00569  -0.0919   0.4834   0.0219
  -0.250   0.5776   0.01383   0.00553  -0.0915   0.4823   0.0228
   0.000   0.6034   0.01367   0.00537  -0.0912   0.4812   0.0236
   0.250   0.6291   0.01353   0.00522  -0.0908   0.4798   0.0242
   0.500   0.6545   0.01335   0.00507  -0.0904   0.4788   0.0250
   0.750   0.6804   0.01325   0.00498  -0.0901   0.4778   0.0259
   1.000   0.7066   0.01318   0.00491  -0.0899   0.4767   0.0276
   1.250   0.7326   0.01310   0.00482  -0.0896   0.4756   0.0289
   1.500   0.7586   0.01302   0.00473  -0.0893   0.4744   0.0304
   1.750   0.7848   0.01299   0.00469  -0.0891   0.4734   0.0320
   2.000   0.8109   0.01296   0.00464  -0.0889   0.4724   0.0350
   2.250   0.8371   0.01296   0.00462  -0.0887   0.4713   0.0396
   2.500   0.8558   0.01226   0.00470  -0.0874   0.4702   0.3632
   2.750   0.8624   0.01125   0.00486  -0.0835   0.4693   0.7509
   3.250   1.0291   0.01135   0.00539  -0.1071   0.4656   0.9960
   3.500   1.0726   0.01143   0.00545  -0.1107   0.4640   1.0000
   3.750   1.0943   0.01150   0.00551  -0.1097   0.4623   1.0000
   4.000   1.1160   0.01157   0.00556  -0.1087   0.4606   1.0000
   4.250   1.1376   0.01163   0.00560  -0.1077   0.4588   1.0000
   4.500   1.1593   0.01172   0.00567  -0.1068   0.4574   1.0000
   4.750   1.1809   0.01180   0.00572  -0.1057   0.4559   1.0000
   5.000   1.2023   0.01191   0.00583  -0.1048   0.4541   1.0000
   5.250   1.2239   0.01202   0.00597  -0.1038   0.4521   1.0000
   5.500   1.2455   0.01213   0.00611  -0.1029   0.4502   1.0000
   5.750   1.2668   0.01224   0.00624  -0.1019   0.4482   1.0000
   6.000   1.2878   0.01235   0.00636  -0.1008   0.4461   1.0000
   6.250   1.3084   0.01246   0.00647  -0.0997   0.4441   1.0000
   6.500   1.3281   0.01256   0.00656  -0.0984   0.4417   1.0000
   6.750   1.3477   0.01269   0.00668  -0.0972   0.4395   1.0000
   7.000   1.3674   0.01283   0.00688  -0.0959   0.4360   1.0000
   7.250   1.3857   0.01296   0.00704  -0.0945   0.4319   1.0000
   7.500   1.4015   0.01310   0.00718  -0.0925   0.4277   1.0000
   7.750   1.4141   0.01326   0.00732  -0.0899   0.4241   1.0000
   8.000   1.4292   0.01343   0.00755  -0.0879   0.4190   1.0000
   8.250   1.4422   0.01364   0.00777  -0.0855   0.4136   1.0000
   8.500   1.4547   0.01390   0.00802  -0.0832   0.4085   1.0000
   8.750   1.4696   0.01418   0.00833  -0.0814   0.4021   1.0000
   9.000   1.4798   0.01458   0.00872  -0.0789   0.3943   1.0000
   9.250   1.4896   0.01506   0.00921  -0.0766   0.3835   1.0000
   9.500   1.4927   0.01584   0.00994  -0.0735   0.3698   1.0000
   9.750   1.4933   0.01688   0.01093  -0.0703   0.3583   1.0000
  10.000   1.4877   0.01840   0.01240  -0.0669   0.3463   1.0000
  10.250   1.4858   0.01997   0.01396  -0.0643   0.3383   1.0000
  10.500   1.4861   0.02158   0.01559  -0.0623   0.3321   1.0000
  10.750   1.4885   0.02319   0.01723  -0.0607   0.3269   1.0000
  11.000   1.4873   0.02514   0.01921  -0.0590   0.3220   1.0000
  11.250   1.4846   0.02731   0.02141  -0.0574   0.3174   1.0000
  11.500   1.4868   0.02925   0.02342  -0.0563   0.3118   1.0000
  11.750   1.4795   0.03210   0.02631  -0.0549   0.3051   1.0000
  12.000   1.4743   0.03481   0.02905  -0.0537   0.2996   1.0000
  12.250   1.4704   0.03748   0.03177  -0.0527   0.2914   1.0000
  12.500   1.4604   0.04073   0.03505  -0.0516   0.2838   1.0000
  12.750   1.4504   0.04406   0.03838  -0.0505   0.2731   1.0000
  13.000   1.4343   0.04797   0.04226  -0.0493   0.2615   1.0000
  13.250   1.4276   0.05100   0.04530  -0.0484   0.2564   1.0000
  13.500   1.4192   0.05421   0.04849  -0.0475   0.2483   1.0000
  13.750   1.4159   0.05699   0.05127  -0.0469   0.2437   1.0000
  14.000   1.4183   0.05919   0.05348  -0.0464   0.2400   1.0000
  14.250   1.4241   0.06108   0.05541  -0.0460   0.2371   1.0000
  14.500   1.4293   0.06306   0.05743  -0.0457   0.2342   1.0000
  14.750   1.4340   0.06508   0.05948  -0.0454   0.2312   1.0000
  15.000   1.4403   0.06693   0.06135  -0.0451   0.2287   1.0000
  15.250   1.4448   0.06896   0.06338  -0.0448   0.2256   1.0000
  15.500   1.4521   0.07079   0.06527  -0.0447   0.2229   1.0000
  15.750   1.4578   0.07278   0.06733  -0.0445   0.2186   1.0000
  16.000   1.4645   0.07466   0.06924  -0.0444   0.2154   1.0000
  16.250   1.4690   0.07676   0.07136  -0.0442   0.2117   1.0000
  16.500   1.4719   0.07908   0.07370  -0.0441   0.2083   1.0000
  16.750   1.4803   0.08083   0.07553  -0.0441   0.2052   1.0000
  17.000   1.4858   0.08289   0.07764  -0.0441   0.2000   1.0000
  17.250   1.4841   0.08577   0.08052  -0.0441   0.1929   1.0000
  17.500   1.4890   0.08793   0.08275  -0.0441   0.1874   1.0000
  17.750   1.4832   0.09138   0.08616  -0.0441   0.1757   1.0000
  18.000   1.4743   0.09522   0.08997  -0.0442   0.1655   1.0000
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