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USA 28 AIRFOIL (usa28-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 28 AIRFOIL (usa28-il)
Reynolds number: 200,000
Max Cl/Cd: 72.07 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa28-il-200000-n5.txt
Download as CSV file: xf-usa28-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 28 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6241   0.08604   0.08213  -0.0584   1.0000   0.0286
 -13.000  -0.6823   0.07271   0.06866  -0.0662   1.0000   0.0281
 -12.750  -0.7218   0.06377   0.05959  -0.0714   1.0000   0.0278
 -12.500  -0.7526   0.05674   0.05244  -0.0754   1.0000   0.0278
 -12.250  -0.7798   0.05041   0.04597  -0.0795   1.0000   0.0278
 -12.000  -0.8067   0.04499   0.04038  -0.0829   1.0000   0.0278
 -11.750  -0.8323   0.04252   0.03778  -0.0794   1.0000   0.0278
 -11.500  -0.8525   0.04062   0.03572  -0.0749   1.0000   0.0282
 -11.250  -0.8603   0.03850   0.03338  -0.0722   0.9992   0.0287
 -11.000  -0.8413   0.03575   0.03026  -0.0746   0.9941   0.0297
 -10.750  -0.8182   0.03420   0.02865  -0.0761   0.9892   0.0308
 -10.500  -0.7910   0.03296   0.02731  -0.0780   0.9852   0.0321
 -10.250  -0.7694   0.03159   0.02577  -0.0785   0.9789   0.0334
 -10.000  -0.7452   0.03014   0.02407  -0.0794   0.9738   0.0348
  -9.750  -0.7250   0.02882   0.02247  -0.0792   0.9669   0.0360
  -9.500  -0.7040   0.02753   0.02097  -0.0790   0.9607   0.0371
  -9.250  -0.6827   0.02626   0.01965  -0.0788   0.9544   0.0385
  -9.000  -0.6605   0.02535   0.01865  -0.0785   0.9479   0.0397
  -8.750  -0.6363   0.02446   0.01766  -0.0784   0.9419   0.0410
  -8.500  -0.6108   0.02357   0.01664  -0.0785   0.9365   0.0426
  -8.250  -0.5876   0.02269   0.01559  -0.0780   0.9298   0.0438
  -8.000  -0.5592   0.02185   0.01459  -0.0785   0.9260   0.0450
  -7.750  -0.5358   0.02096   0.01361  -0.0780   0.9199   0.0463
  -7.500  -0.5106   0.02001   0.01262  -0.0779   0.9147   0.0479
  -7.250  -0.4808   0.01922   0.01174  -0.0787   0.9113   0.0493
  -7.000  -0.4532   0.01854   0.01099  -0.0789   0.9063   0.0510
  -6.750  -0.4252   0.01792   0.01027  -0.0791   0.9008   0.0527
  -6.500  -0.3923   0.01732   0.00956  -0.0803   0.8971   0.0551
  -6.250  -0.3571   0.01664   0.00877  -0.0821   0.8942   0.0578
  -6.000  -0.3312   0.01605   0.00813  -0.0819   0.8865   0.0614
  -5.750  -0.2941   0.01549   0.00746  -0.0840   0.8815   0.0658
  -5.500  -0.2566   0.01495   0.00682  -0.0862   0.8758   0.0716
  -5.250  -0.2230   0.01440   0.00624  -0.0875   0.8679   0.0827
  -5.000  -0.1844   0.01376   0.00583  -0.0902   0.8621   0.1267
  -4.750  -0.1547   0.01357   0.00558  -0.0906   0.8534   0.1505
  -4.500  -0.1167   0.01331   0.00526  -0.0929   0.8471   0.1674
  -4.250  -0.0898   0.01313   0.00505  -0.0927   0.8379   0.1788
  -4.000  -0.0552   0.01291   0.00479  -0.0941   0.8311   0.1900
  -3.750  -0.0303   0.01276   0.00463  -0.0935   0.8220   0.2019
  -3.500   0.0012   0.01256   0.00444  -0.0943   0.8151   0.2190
  -3.250   0.0250   0.01242   0.00434  -0.0935   0.8057   0.2358
  -2.750   0.0781   0.01222   0.00420  -0.0928   0.7881   0.2789
  -2.500   0.1046   0.01219   0.00416  -0.0925   0.7800   0.2985
  -2.250   0.1304   0.01218   0.00412  -0.0919   0.7715   0.3137
  -2.000   0.1557   0.01218   0.00408  -0.0912   0.7625   0.3262
  -1.750   0.1823   0.01219   0.00402  -0.0908   0.7539   0.3379
  -1.500   0.2070   0.01221   0.00398  -0.0900   0.7453   0.3487
  -1.250   0.2337   0.01221   0.00394  -0.0896   0.7372   0.3575
  -1.000   0.2576   0.01222   0.00390  -0.0887   0.7275   0.3655
  -0.750   0.2832   0.01222   0.00386  -0.0881   0.7187   0.3724
  -0.500   0.3084   0.01225   0.00380  -0.0874   0.7090   0.3795
  -0.250   0.3331   0.01223   0.00378  -0.0866   0.6999   0.3851
   0.000   0.3593   0.01225   0.00374  -0.0861   0.6920   0.3913
   0.250   0.3841   0.01226   0.00373  -0.0854   0.6840   0.3968
   0.500   0.4102   0.01227   0.00372  -0.0849   0.6765   0.4027
   0.750   0.4348   0.01232   0.00374  -0.0842   0.6686   0.4100
   1.000   0.4604   0.01233   0.00375  -0.0836   0.6609   0.4166
   1.250   0.4847   0.01237   0.00379  -0.0828   0.6526   0.4240
   1.750   0.5337   0.01243   0.00387  -0.0813   0.6356   0.4367
   2.000   0.5591   0.01249   0.00391  -0.0807   0.6278   0.4428
   2.250   0.5820   0.01250   0.00399  -0.0796   0.6188   0.4495
   2.500   0.6061   0.01257   0.00406  -0.0787   0.6100   0.4573
   2.750   0.6282   0.01259   0.00414  -0.0775   0.5997   0.4646
   3.000   0.6506   0.01264   0.00424  -0.0763   0.5894   0.4730
   3.250   0.6726   0.01267   0.00432  -0.0750   0.5789   0.4827
   3.500   0.6932   0.01269   0.00442  -0.0735   0.5667   0.4932
   3.750   0.7132   0.01271   0.00453  -0.0718   0.5530   0.5058
   4.000   0.7333   0.01271   0.00464  -0.0701   0.5386   0.5273
   4.250   0.8879   0.01256   0.00553  -0.0982   0.5071   0.9891
   4.500   0.9276   0.01287   0.00576  -0.1010   0.4901   1.0000
   4.750   0.9452   0.01312   0.00596  -0.0988   0.4773   1.0000
   5.000   0.9622   0.01340   0.00616  -0.0966   0.4646   1.0000
   5.250   0.9790   0.01371   0.00640  -0.0943   0.4524   1.0000
   5.500   0.9961   0.01405   0.00668  -0.0921   0.4420   1.0000
   5.750   1.0155   0.01432   0.00697  -0.0905   0.4340   1.0000
   6.000   1.0346   0.01465   0.00727  -0.0887   0.4270   1.0000
   6.250   1.0542   0.01491   0.00758  -0.0871   0.4199   1.0000
   6.500   1.0715   0.01529   0.00791  -0.0850   0.4106   1.0000
   6.750   1.0851   0.01562   0.00826  -0.0822   0.3959   1.0000
   7.000   1.0954   0.01598   0.00858  -0.0787   0.3783   1.0000
   7.250   1.1036   0.01625   0.00886  -0.0747   0.3599   1.0000
   7.500   1.1132   0.01653   0.00915  -0.0712   0.3412   1.0000
   7.750   1.1212   0.01687   0.00947  -0.0673   0.3175   1.0000
   8.000   1.1257   0.01737   0.00984  -0.0630   0.2834   1.0000
   8.250   1.1245   0.01818   0.01042  -0.0579   0.2401   1.0000
   8.500   1.1221   0.01923   0.01122  -0.0529   0.1976   1.0000
   8.750   1.1195   0.02046   0.01219  -0.0482   0.1555   1.0000
   9.000   1.1166   0.02180   0.01329  -0.0437   0.1127   1.0000
   9.250   1.1128   0.02330   0.01454  -0.0394   0.0747   1.0000
   9.500   1.1103   0.02482   0.01589  -0.0355   0.0473   1.0000
   9.750   1.1127   0.02614   0.01717  -0.0324   0.0371   1.0000
  10.000   1.1166   0.02745   0.01849  -0.0296   0.0318   1.0000
  10.250   1.1223   0.02869   0.01982  -0.0272   0.0287   1.0000
  10.500   1.1257   0.03015   0.02133  -0.0248   0.0265   1.0000
  10.750   1.1311   0.03153   0.02280  -0.0227   0.0249   1.0000
  11.000   1.1359   0.03302   0.02439  -0.0207   0.0237   1.0000
  11.250   1.1395   0.03464   0.02611  -0.0187   0.0226   1.0000
  11.500   1.1428   0.03635   0.02791  -0.0170   0.0217   1.0000
  11.750   1.1416   0.03851   0.03014  -0.0151   0.0207   1.0000
  12.000   1.1416   0.04066   0.03238  -0.0136   0.0200   1.0000
  12.250   1.1425   0.04281   0.03463  -0.0122   0.0196   1.0000
  12.500   1.1462   0.04477   0.03672  -0.0111   0.0187   1.0000
  12.750   1.1468   0.04709   0.03914  -0.0100   0.0180   1.0000
  13.000   1.1471   0.04951   0.04165  -0.0091   0.0177   1.0000
  13.250   1.1475   0.05198   0.04421  -0.0083   0.0171   1.0000
  13.500   1.1479   0.05452   0.04683  -0.0076   0.0168   1.0000
  13.750   1.1481   0.05712   0.04951  -0.0069   0.0165   1.0000
  14.000   1.1469   0.05991   0.05236  -0.0064   0.0160   1.0000
  14.250   1.1465   0.06264   0.05514  -0.0058   0.0157   1.0000
  14.500   1.1467   0.06531   0.05785  -0.0052   0.0154   1.0000
  14.750   1.1494   0.06781   0.06046  -0.0048   0.0150   1.0000
  15.000   1.1521   0.07036   0.06315  -0.0045   0.0146   1.0000
  15.250   1.1546   0.07295   0.06586  -0.0043   0.0143   1.0000
  15.500   1.1566   0.07568   0.06870  -0.0042   0.0139   1.0000
  15.750   1.1585   0.07842   0.07156  -0.0042   0.0135   1.0000
  16.000   1.1604   0.08120   0.07444  -0.0040   0.0133   1.0000
  16.250   1.1613   0.08416   0.07752  -0.0042   0.0131   1.0000
  16.500   1.1613   0.08729   0.08076  -0.0045   0.0128   1.0000
  16.750   1.1615   0.09046   0.08404  -0.0048   0.0126   1.0000
  17.000   1.1606   0.09383   0.08751  -0.0053   0.0124   1.0000
  17.250   1.1592   0.09733   0.09113  -0.0060   0.0122   1.0000
  17.500   1.1572   0.10094   0.09486  -0.0068   0.0121   1.0000
  17.750   1.1546   0.10470   0.09874  -0.0079   0.0119   1.0000
  18.000   1.1512   0.10864   0.10280  -0.0090   0.0118   1.0000
  18.250   1.1467   0.11280   0.10707  -0.0103   0.0117   1.0000
  18.500   1.1408   0.11732   0.11173  -0.0118   0.0116   1.0000
  19.000   1.1221   0.12799   0.12273  -0.0165   0.0114   1.0000
  19.250   1.1111   0.13396   0.12888  -0.0196   0.0114   1.0000
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