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 smoothed (ua2-180sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: UA(2)-180 smoothed (ua2-180sm-il)
Reynolds number: 500,000
Max Cl/Cd: 102.9 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ua2-180sm-il-500000.txt
Download as CSV file: xf-ua2-180sm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: UA(2)-180 smoothed                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.0953   0.09735   0.09297  -0.0861   0.5431   0.0211
 -10.750   0.0882   0.09283   0.08847  -0.0889   0.5427   0.0213
 -10.500   0.0895   0.08887   0.08451  -0.0903   0.5421   0.0214
 -10.250   0.0988   0.08615   0.08179  -0.0905   0.5413   0.0216
 -10.000   0.1096   0.08390   0.07952  -0.0906   0.5405   0.0218
  -9.750   0.1180   0.08145   0.07707  -0.0910   0.5396   0.0221
  -9.500   0.1229   0.07858   0.07419  -0.0919   0.5389   0.0224
  -9.250   0.1274   0.07571   0.07133  -0.0928   0.5380   0.0228
  -9.000   0.1304   0.07267   0.06829  -0.0938   0.5372   0.0232
  -8.750   0.1317   0.06928   0.06493  -0.0950   0.5368   0.0240
  -8.500   0.1115   0.06254   0.05823  -0.0998   0.5367   0.0252
  -8.250   0.0992   0.05685   0.05258  -0.1036   0.5365   0.0253
  -8.000   0.1016   0.05393   0.04970  -0.1031   0.5360   0.0256
  -7.750   0.1016   0.05090   0.04670  -0.1042   0.5355   0.0257
  -7.500   0.0231   0.05377   0.04907  -0.1162   0.5361   0.0253
  -7.250   0.0350   0.05163   0.04705  -0.1157   0.5355   0.0256
  -7.000   0.0428   0.04999   0.04541  -0.1151   0.5349   0.0258
  -6.750   0.0499   0.04806   0.04345  -0.1145   0.5342   0.0260
  -6.500   0.0587   0.04621   0.04155  -0.1139   0.5334   0.0264
  -6.250   0.0672   0.04391   0.03917  -0.1132   0.5325   0.0269
  -6.000   0.0611   0.03940   0.03397  -0.1102   0.5319   0.0298
  -5.750   0.0711   0.03586   0.03038  -0.1094   0.5311   0.0303
  -5.500   0.0895   0.03445   0.02898  -0.1089   0.5302   0.0307
  -5.250   0.1076   0.03314   0.02762  -0.1083   0.5294   0.0313
  -5.000   0.1259   0.03177   0.02612  -0.1074   0.5286   0.0324
  -4.750   0.1380   0.02927   0.02312  -0.1049   0.5279   0.0358
  -4.500   0.1597   0.02807   0.02192  -0.1045   0.5271   0.0365
  -4.250   0.1821   0.02724   0.02103  -0.1040   0.5263   0.0383
  -4.000   0.2011   0.02581   0.01926  -0.1026   0.5255   0.0424
  -3.750   0.2247   0.02495   0.01839  -0.1022   0.5248   0.0440
  -3.500   0.2464   0.02409   0.01721  -0.1011   0.5240   0.0494
  -3.250   0.2710   0.02320   0.01633  -0.1009   0.5232   0.0514
  -3.000   0.2944   0.02263   0.01554  -0.1001   0.5224   0.0582
  -2.750   0.3199   0.02198   0.01491  -0.1000   0.5214   0.0614
  -2.500   0.3490   0.01934   0.01142  -0.0975   0.5201   0.0353
  -2.250   0.3760   0.01850   0.01059  -0.0972   0.5195   0.0346
  -2.000   0.4024   0.01764   0.00973  -0.0969   0.5190   0.0337
  -1.750   0.4286   0.01711   0.00918  -0.0965   0.5183   0.0334
  -1.500   0.4545   0.01673   0.00879  -0.0960   0.5176   0.0334
  -1.250   0.4800   0.01643   0.00849  -0.0956   0.5169   0.0336
  -1.000   0.5055   0.01621   0.00826  -0.0951   0.5161   0.0339
  -0.750   0.5312   0.01606   0.00812  -0.0947   0.5151   0.0347
  -0.500   0.5560   0.01583   0.00789  -0.0942   0.5140   0.0356
  -0.250   0.5808   0.01562   0.00770  -0.0937   0.5130   0.0365
   0.000   0.6064   0.01554   0.00763  -0.0933   0.5121   0.0375
   0.250   0.6324   0.01549   0.00757  -0.0930   0.5111   0.0389
   0.500   0.6588   0.01545   0.00752  -0.0928   0.5100   0.0405
   0.750   0.6853   0.01539   0.00745  -0.0926   0.5089   0.0441
   1.000   0.7121   0.01536   0.00743  -0.0924   0.5078   0.0545
   1.250   0.7226   0.01400   0.00750  -0.0898   0.5068   0.5507
   1.500   0.8208   0.01343   0.00796  -0.1038   0.5053   0.9779
   1.750   0.8928   0.01397   0.00837  -0.1132   0.5034   0.9932
   2.000   0.9535   0.01394   0.00830  -0.1202   0.5024   1.0000
   2.250   0.9742   0.01402   0.00838  -0.1191   0.5013   1.0000
   2.500   0.9952   0.01411   0.00847  -0.1181   0.4999   1.0000
   2.750   1.0164   0.01421   0.00856  -0.1170   0.4985   1.0000
   3.000   1.0379   0.01429   0.00864  -0.1160   0.4969   1.0000
   3.250   1.0597   0.01438   0.00870  -0.1151   0.4954   1.0000
   3.500   1.0821   0.01442   0.00873  -0.1143   0.4938   1.0000
   3.750   1.1054   0.01445   0.00872  -0.1136   0.4923   1.0000
   4.000   1.1296   0.01448   0.00870  -0.1131   0.4908   1.0000
   4.250   1.1547   0.01455   0.00871  -0.1127   0.4893   1.0000
   4.500   1.1794   0.01489   0.00899  -0.1125   0.4874   1.0000
   4.750   1.1995   0.01491   0.00906  -0.1112   0.4860   1.0000
   5.000   1.2200   0.01499   0.00917  -0.1100   0.4844   1.0000
   5.250   1.2405   0.01505   0.00928  -0.1089   0.4824   1.0000
   5.500   1.2620   0.01514   0.00938  -0.1079   0.4807   1.0000
   5.750   1.2842   0.01519   0.00945  -0.1071   0.4790   1.0000
   6.000   1.3078   0.01519   0.00944  -0.1065   0.4772   1.0000
   6.250   1.3326   0.01517   0.00939  -0.1061   0.4756   1.0000
   6.500   1.3583   0.01518   0.00937  -0.1060   0.4741   1.0000
   6.750   1.3846   0.01531   0.00946  -0.1060   0.4725   1.0000
   7.000   1.4037   0.01546   0.00967  -0.1047   0.4707   1.0000
   7.250   1.4208   0.01553   0.00982  -0.1030   0.4684   1.0000
   7.500   1.4398   0.01557   0.00992  -0.1016   0.4660   1.0000
   7.750   1.4609   0.01556   0.00993  -0.1007   0.4636   1.0000
   8.000   1.4836   0.01550   0.00988  -0.1000   0.4615   1.0000
   8.250   1.5075   0.01546   0.00982  -0.0995   0.4596   1.0000
   8.500   1.5321   0.01548   0.00982  -0.0992   0.4575   1.0000
   8.750   1.5460   0.01562   0.01005  -0.0970   0.4549   1.0000
   9.000   1.5595   0.01570   0.01021  -0.0947   0.4517   1.0000
   9.250   1.5758   0.01571   0.01026  -0.0929   0.4486   1.0000
   9.500   1.5925   0.01567   0.01024  -0.0912   0.4458   1.0000
   9.750   1.6104   0.01565   0.01019  -0.0896   0.4430   1.0000
  10.000   1.6128   0.01589   0.01055  -0.0854   0.4392   1.0000
  10.250   1.6215   0.01608   0.01081  -0.0826   0.4349   1.0000
  10.500   1.6344   0.01623   0.01098  -0.0805   0.4310   1.0000
  10.750   1.6459   0.01652   0.01130  -0.0784   0.4267   1.0000
  11.000   1.6537   0.01700   0.01187  -0.0760   0.4207   1.0000
  11.250   1.6642   0.01740   0.01227  -0.0740   0.4152   1.0000
  11.500   1.6706   0.01815   0.01310  -0.0718   0.4075   1.0000
  11.750   1.6760   0.01900   0.01394  -0.0697   0.4001   1.0000
  12.000   1.6787   0.02017   0.01516  -0.0676   0.3908   1.0000
  12.250   1.6786   0.02165   0.01665  -0.0655   0.3816   1.0000
  12.500   1.6733   0.02360   0.01857  -0.0632   0.3721   1.0000
  12.750   1.6657   0.02592   0.02090  -0.0611   0.3622   1.0000
  13.000   1.6557   0.02858   0.02357  -0.0591   0.3529   1.0000
  13.250   1.6419   0.03164   0.02660  -0.0571   0.3436   1.0000
  13.500   1.6292   0.03489   0.02989  -0.0555   0.3344   1.0000
  13.750   1.6188   0.03799   0.03299  -0.0542   0.3266   1.0000
  14.000   1.6104   0.04099   0.03601  -0.0530   0.3192   1.0000
  14.250   1.6047   0.04375   0.03877  -0.0520   0.3126   1.0000
  14.500   1.6006   0.04646   0.04152  -0.0512   0.3063   1.0000
  14.750   1.6005   0.04862   0.04362  -0.0503   0.3004   1.0000
  15.000   1.5967   0.05144   0.04654  -0.0498   0.2949   1.0000
  15.250   1.5971   0.05373   0.04882  -0.0492   0.2894   1.0000
  15.500   1.6021   0.05549   0.05056  -0.0486   0.2848   1.0000
  15.750   1.6014   0.05805   0.05322  -0.0482   0.2802   1.0000
  16.000   1.6050   0.06008   0.05526  -0.0478   0.2756   1.0000
  16.250   1.6155   0.06123   0.05636  -0.0474   0.2714   1.0000
  16.500   1.6106   0.06436   0.05961  -0.0472   0.2666   1.0000
  16.750   1.6133   0.06655   0.06183  -0.0469   0.2622   1.0000
  17.000   1.6180   0.06840   0.06363  -0.0466   0.2563   1.0000
  17.250   1.6149   0.07140   0.06674  -0.0465   0.2521   1.0000
  17.500   1.6168   0.07375   0.06913  -0.0463   0.2475   1.0000
  17.750   1.6245   0.07529   0.07063  -0.0461   0.2431   1.0000
  18.000   1.6223   0.07821   0.07365  -0.0461   0.2390   1.0000
  18.250   1.6225   0.08080   0.07632  -0.0461   0.2345   1.0000
  18.500   1.6249   0.08304   0.07850  -0.0460   0.2289   1.0000
  18.750   1.6162   0.08686   0.08244  -0.0461   0.2229   1.0000
  19.000   1.6161   0.08952   0.08512  -0.0462   0.2177   1.0000
  19.250   1.6154   0.09220   0.08781  -0.0463   0.2129   1.0000
<< Back to UA(2)-180 smoothed (ua2-180sm-il)

Polar data table (+)

Polar graphs


<< Back to UA(2)-180 smoothed (ua2-180sm-il)