Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

UA(2)-180 (University of Alberta/Marsden) (ua2-180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: UA(2)-180 (University of Alberta/Marsden) (ua2-180-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.19 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ua2-180-il-1000000.txt
Download as CSV file: xf-ua2-180-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1059   0.09055   0.08681  -0.0906   0.5164   0.0154
 -10.500   0.1087   0.08696   0.08322  -0.0920   0.5159   0.0154
 -10.250   0.1106   0.08317   0.07944  -0.0934   0.5155   0.0154
 -10.000   0.1125   0.07929   0.07558  -0.0944   0.5149   0.0155
  -9.750   0.1187   0.07650   0.07279  -0.0949   0.5143   0.0156
  -9.500   0.1250   0.07381   0.07011  -0.0955   0.5137   0.0157
  -9.250   0.1321   0.07136   0.06766  -0.0960   0.5130   0.0158
  -9.000   0.1370   0.06855   0.06486  -0.0968   0.5124   0.0159
  -8.750   0.1405   0.06557   0.06190  -0.0976   0.5117   0.0160
  -8.500   0.1436   0.06263   0.05897  -0.0985   0.5112   0.0161
  -8.250   0.1453   0.05953   0.05589  -0.0995   0.5105   0.0162
  -8.000   0.1465   0.05647   0.05283  -0.1004   0.5097   0.0164
  -7.750   0.1447   0.05303   0.04941  -0.1017   0.5092   0.0165
  -7.500   0.1417   0.04963   0.04603  -0.1030   0.5087   0.0167
  -7.250   0.1354   0.04610   0.04253  -0.1048   0.5079   0.0170
  -7.000   0.1144   0.04204   0.03849  -0.1075   0.5072   0.0170
  -6.750   0.1006   0.03807   0.03450  -0.1085   0.5069   0.0170
  -6.500   0.0956   0.03406   0.03041  -0.1094   0.5063   0.0173
  -6.250   0.0942   0.03010   0.02633  -0.1095   0.5054   0.0176
  -6.000   0.0760   0.02202   0.01763  -0.1071   0.5049   0.0185
  -5.750   0.0796   0.03113   0.02627  -0.1101   0.5051   0.0188
  -5.500   0.0963   0.02968   0.02474  -0.1093   0.5036   0.0189
  -5.250   0.1152   0.02861   0.02363  -0.1086   0.5026   0.0191
  -5.000   0.1341   0.02734   0.02227  -0.1078   0.5021   0.0193
  -4.750   0.1543   0.02627   0.02113  -0.1070   0.5017   0.0197
  -4.500   0.1739   0.02483   0.01954  -0.1059   0.5011   0.0202
  -4.250   0.1942   0.02414   0.01831  -0.1034   0.5006   0.0220
  -4.000   0.2150   0.02307   0.01703  -0.1022   0.5000   0.0220
  -3.750   0.2338   0.02009   0.01399  -0.1013   0.4993   0.0225
  -3.500   0.2581   0.01921   0.01307  -0.1009   0.4986   0.0228
  -3.250   0.2828   0.01848   0.01229  -0.1005   0.4978   0.0233
  -3.000   0.3079   0.01784   0.01156  -0.1000   0.4970   0.0243
  -2.750   0.3339   0.01855   0.01191  -0.0989   0.4959   0.0258
  -2.500   0.3580   0.01621   0.00957  -0.0985   0.4948   0.0266
  -2.250   0.3842   0.01551   0.00885  -0.0983   0.4934   0.0274
  -2.000   0.4117   0.01432   0.00732  -0.0972   0.4921   0.0222
  -1.750   0.4380   0.01354   0.00652  -0.0969   0.4911   0.0225
  -1.500   0.4644   0.01306   0.00603  -0.0966   0.4900   0.0226
  -1.250   0.4908   0.01278   0.00577  -0.0964   0.4889   0.0232
  -1.000   0.5174   0.01260   0.00558  -0.0962   0.4877   0.0240
  -0.750   0.5440   0.01247   0.00543  -0.0960   0.4865   0.0247
  -0.500   0.5702   0.01221   0.00517  -0.0956   0.4860   0.0251
  -0.250   0.5973   0.01209   0.00503  -0.0954   0.4854   0.0257
   0.000   0.6221   0.01173   0.00470  -0.0949   0.4848   0.0262
   0.250   0.6475   0.01148   0.00447  -0.0944   0.4839   0.0270
   0.500   0.6739   0.01134   0.00434  -0.0942   0.4832   0.0278
   0.750   0.7006   0.01125   0.00426  -0.0940   0.4823   0.0293
   1.000   0.7277   0.01119   0.00420  -0.0939   0.4814   0.0301
   1.250   0.7536   0.01102   0.00404  -0.0936   0.4805   0.0314
   1.500   0.7804   0.01094   0.00396  -0.0935   0.4796   0.0329
   1.750   0.8073   0.01088   0.00390  -0.0934   0.4785   0.0344
   2.000   0.8341   0.01082   0.00383  -0.0932   0.4774   0.0369
   2.250   0.8610   0.01078   0.00379  -0.0931   0.4765   0.0412
   2.500   0.8769   0.00988   0.00386  -0.0913   0.4756   0.4512
   2.750   0.8799   0.00881   0.00400  -0.0863   0.4746   0.8704
   3.000   1.0015   0.00907   0.00434  -0.1064   0.4724   0.9889
   3.250   1.0569   0.00926   0.00448  -0.1124   0.4709   0.9955
   3.500   1.1139   0.00926   0.00446  -0.1189   0.4699   0.9998
   3.750   1.1387   0.00928   0.00449  -0.1185   0.4687   1.0000
   4.000   1.1610   0.00931   0.00452  -0.1176   0.4674   1.0000
   4.250   1.1833   0.00934   0.00455  -0.1167   0.4660   1.0000
   4.500   1.2058   0.00938   0.00459  -0.1159   0.4645   1.0000
   4.750   1.2283   0.00942   0.00463  -0.1150   0.4631   1.0000
   5.000   1.2507   0.00945   0.00466  -0.1142   0.4616   1.0000
   5.250   1.2730   0.00950   0.00470  -0.1133   0.4600   1.0000
   5.500   1.2949   0.00958   0.00475  -0.1124   0.4580   1.0000
   5.750   1.3173   0.00971   0.00486  -0.1116   0.4559   1.0000
   6.000   1.3391   0.00973   0.00492  -0.1106   0.4543   1.0000
   6.250   1.3611   0.00977   0.00499  -0.1097   0.4522   1.0000
   6.500   1.3831   0.00982   0.00506  -0.1089   0.4499   1.0000
   6.750   1.4048   0.00988   0.00513  -0.1079   0.4475   1.0000
   7.000   1.4259   0.00995   0.00520  -0.1069   0.4452   1.0000
   7.250   1.4461   0.01006   0.00530  -0.1057   0.4428   1.0000
   7.500   1.4669   0.01018   0.00543  -0.1047   0.4404   1.0000
   7.750   1.4885   0.01025   0.00554  -0.1038   0.4379   1.0000
   8.000   1.5093   0.01034   0.00566  -0.1028   0.4346   1.0000
   8.250   1.5277   0.01045   0.00578  -0.1013   0.4305   1.0000
   8.500   1.5402   0.01061   0.00591  -0.0986   0.4265   1.0000
   8.750   1.5592   0.01071   0.00606  -0.0972   0.4229   1.0000
   9.000   1.5748   0.01085   0.00622  -0.0953   0.4172   1.0000
   9.250   1.5877   0.01108   0.00643  -0.0929   0.4120   1.0000
   9.500   1.6058   0.01127   0.00665  -0.0916   0.4054   1.0000
   9.750   1.6177   0.01161   0.00697  -0.0892   0.3960   1.0000
  10.000   1.6272   0.01208   0.00740  -0.0867   0.3827   1.0000
  10.250   1.6302   0.01284   0.00809  -0.0833   0.3652   1.0000
  10.500   1.6289   0.01390   0.00907  -0.0796   0.3497   1.0000
  10.750   1.6292   0.01505   0.01018  -0.0764   0.3394   1.0000
  11.000   1.6367   0.01598   0.01113  -0.0745   0.3328   1.0000
  11.250   1.6357   0.01746   0.01259  -0.0718   0.3250   1.0000
  11.500   1.6463   0.01840   0.01358  -0.0706   0.3202   1.0000
  11.750   1.6519   0.01973   0.01494  -0.0691   0.3150   1.0000
  12.000   1.6489   0.02172   0.01694  -0.0671   0.3087   1.0000
  12.250   1.6576   0.02299   0.01827  -0.0661   0.3032   1.0000
  12.500   1.6553   0.02514   0.02044  -0.0645   0.2967   1.0000
  12.750   1.6483   0.02778   0.02311  -0.0629   0.2870   1.0000
  13.000   1.6314   0.03154   0.02688  -0.0611   0.2768   1.0000
  13.250   1.6217   0.03472   0.03011  -0.0598   0.2697   1.0000
  13.500   1.5938   0.03963   0.03501  -0.0578   0.2588   1.0000
  13.750   1.5861   0.04268   0.03811  -0.0568   0.2553   1.0000
  14.000   1.5661   0.04690   0.04233  -0.0553   0.2483   1.0000
  14.250   1.5625   0.04958   0.04504  -0.0544   0.2449   1.0000
  14.500   1.5527   0.05285   0.04832  -0.0534   0.2399   1.0000
  14.750   1.5453   0.05596   0.05143  -0.0526   0.2351   1.0000
  15.000   1.5527   0.05766   0.05318  -0.0523   0.2332   1.0000
  15.250   1.5575   0.05962   0.05518  -0.0519   0.2305   1.0000
  15.500   1.5592   0.06192   0.05751  -0.0515   0.2273   1.0000
  15.750   1.5596   0.06433   0.05992  -0.0510   0.2235   1.0000
  16.000   1.5624   0.06651   0.06212  -0.0507   0.2204   1.0000
  16.250   1.5689   0.06838   0.06405  -0.0505   0.2183   1.0000
  16.500   1.5771   0.07007   0.06580  -0.0504   0.2157   1.0000
  16.750   1.5847   0.07180   0.06757  -0.0503   0.2131   1.0000
  17.000   1.5862   0.07417   0.06994  -0.0500   0.2084   1.0000
  17.250   1.5863   0.07676   0.07255  -0.0498   0.2045   1.0000
  17.500   1.5952   0.07841   0.07426  -0.0498   0.2016   1.0000
  17.750   1.5984   0.08066   0.07653  -0.0498   0.1949   1.0000
  18.000   1.5988   0.08321   0.07908  -0.0497   0.1888   1.0000
  18.250   1.5967   0.08610   0.08197  -0.0496   0.1806   1.0000
  18.500   1.5939   0.08906   0.08492  -0.0495   0.1724   1.0000
  18.750   1.5863   0.09263   0.08847  -0.0495   0.1644   1.0000
  19.000   1.5799   0.09604   0.09185  -0.0495   0.1562   1.0000
<< Back to UA(2)-180 (University of Alberta/Marsden) (ua2-180-il)

Polar data table (+)

Polar graphs


<< Back to UA(2)-180 (University of Alberta/Marsden) (ua2-180-il)