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USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 32 AIRFOIL (usa32-il)
Reynolds number: 200,000
Max Cl/Cd: 50.48 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa32-il-200000-n5.txt
Download as CSV file: xf-usa32-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 32 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1668   0.10861   0.10442  -0.1362   0.9137   0.0334
 -11.250   0.1684   0.10577   0.10158  -0.1382   0.9094   0.0344
 -11.000   0.1719   0.10248   0.09828  -0.1418   0.9065   0.0346
 -10.750   0.1864   0.09905   0.09486  -0.1442   0.9048   0.0348
 -10.500   0.2092   0.09621   0.09200  -0.1455   0.9035   0.0355
 -10.250   0.2292   0.09347   0.08924  -0.1484   0.9022   0.0369
 -10.000   0.2395   0.09080   0.08657  -0.1507   0.8992   0.0388
  -9.750   0.2225   0.08863   0.08443  -0.1515   0.8914   0.0400
  -9.500   0.2388   0.08526   0.08105  -0.1540   0.8884   0.0404
  -9.250   0.2660   0.08266   0.07843  -0.1558   0.8866   0.0414
  -9.000   0.2905   0.07955   0.07528  -0.1604   0.8846   0.0430
  -8.750   0.2838   0.07823   0.07400  -0.1575   0.8769   0.0434
  -8.500   0.2889   0.07552   0.07129  -0.1595   0.8712   0.0450
  -8.250   0.2872   0.07096   0.06670  -0.1668   0.8662   0.0461
  -8.000   0.2599   0.07038   0.06619  -0.1601   0.8559   0.0462
  -7.750   0.2862   0.06857   0.06438  -0.1599   0.8529   0.0473
  -7.250   0.2475   0.06309   0.05890  -0.1538   0.8358   0.0397
  -6.750   0.2510   0.06099   0.05683  -0.1486   0.8208   0.0425
  -6.250   0.1980   0.05058   0.04626  -0.1428   0.7989   0.0350
  -6.000   0.2091   0.05060   0.04629  -0.1402   0.7906   0.0358
  -5.750   0.1265   0.03355   0.02827  -0.1352   0.7716   0.0348
  -5.500   0.1361   0.03047   0.02475  -0.1335   0.7631   0.0348
  -5.250   0.1378   0.02887   0.02291  -0.1292   0.7500   0.0350
  -5.000   0.1512   0.02727   0.02108  -0.1270   0.7393   0.0353
  -4.750   0.1738   0.02573   0.01927  -0.1263   0.7298   0.0356
  -4.500   0.1933   0.02461   0.01794  -0.1249   0.7167   0.0362
  -4.250   0.2182   0.02347   0.01651  -0.1244   0.7043   0.0371
  -4.000   0.2453   0.02223   0.01488  -0.1242   0.6930   0.0377
  -3.750   0.2725   0.02119   0.01349  -0.1239   0.6826   0.0380
  -3.500   0.2982   0.02037   0.01236  -0.1233   0.6739   0.0384
  -3.250   0.3256   0.01969   0.01138  -0.1230   0.6659   0.0388
  -3.000   0.3515   0.01915   0.01061  -0.1225   0.6588   0.0391
  -2.750   0.3775   0.01874   0.00999  -0.1220   0.6517   0.0396
  -2.250   0.4302   0.01794   0.00897  -0.1212   0.6403   0.0412
  -2.000   0.4553   0.01766   0.00863  -0.1206   0.6346   0.0417
  -1.750   0.4840   0.01740   0.00826  -0.1207   0.6292   0.0423
  -1.500   0.5080   0.01723   0.00805  -0.1199   0.6244   0.0428
  -1.250   0.5295   0.01711   0.00791  -0.1185   0.6193   0.0434
  -1.000   0.5542   0.01702   0.00776  -0.1178   0.6143   0.0440
  -0.750   0.5834   0.01694   0.00758  -0.1180   0.6098   0.0449
  -0.500   0.6036   0.01692   0.00753  -0.1165   0.6051   0.0458
  -0.250   0.6233   0.01689   0.00749  -0.1148   0.6001   0.0470
   0.000   0.6473   0.01686   0.00741  -0.1141   0.5954   0.0489
   0.250   0.6760   0.01684   0.00729  -0.1142   0.5909   0.0511
   0.500   0.6942   0.01687   0.00730  -0.1123   0.5858   0.0527
   0.750   0.7127   0.01689   0.00732  -0.1104   0.5805   0.0549
   1.000   0.7352   0.01688   0.00729  -0.1093   0.5755   0.0599
   1.250   0.7627   0.01659   0.00735  -0.1095   0.5710   0.1676
   1.500   0.7765   0.01674   0.00759  -0.1068   0.5657   0.2011
   1.750   0.7931   0.01691   0.00779  -0.1046   0.5600   0.2213
   2.000   0.8133   0.01706   0.00790  -0.1032   0.5548   0.2325
   2.250   0.8298   0.01723   0.00808  -0.1010   0.5490   0.2414
   2.500   0.8441   0.01743   0.00829  -0.0985   0.5424   0.2491
   2.750   0.8621   0.01760   0.00841  -0.0967   0.5364   0.2581
   3.000   0.8766   0.01782   0.00868  -0.0942   0.5298   0.2664
   3.250   0.8914   0.01805   0.00890  -0.0919   0.5229   0.2762
   3.500   0.9080   0.01826   0.00911  -0.0899   0.5168   0.2834
   3.750   0.9223   0.01850   0.00937  -0.0876   0.5092   0.2896
   4.000   0.9381   0.01872   0.00953  -0.0855   0.5021   0.2943
   4.250   0.9531   0.01896   0.00980  -0.0834   0.4943   0.2980
   4.500   0.9681   0.01922   0.01004  -0.0812   0.4864   0.3025
   4.750   0.9836   0.01951   0.01031  -0.0793   0.4789   0.3073
   5.000   0.9990   0.01982   0.01057  -0.0773   0.4713   0.3132
   5.250   1.0156   0.02012   0.01087  -0.0756   0.4644   0.3181
   5.500   1.0319   0.02047   0.01122  -0.0739   0.4573   0.3247
   5.750   1.0487   0.02083   0.01150  -0.0724   0.4510   0.3319
   6.000   1.0665   0.02119   0.01189  -0.0710   0.4447   0.3373
   6.250   1.0844   0.02156   0.01225  -0.0698   0.4387   0.3441
   6.500   1.1033   0.02194   0.01256  -0.0687   0.4336   0.3504
   6.750   1.1209   0.02235   0.01301  -0.0675   0.4277   0.3572
   7.000   1.1375   0.02281   0.01344  -0.0661   0.4215   0.3643
   7.250   1.1567   0.02320   0.01380  -0.0652   0.4167   0.3708
   7.500   1.1729   0.02369   0.01431  -0.0638   0.4109   0.3787
   7.750   1.1898   0.02417   0.01480  -0.0626   0.4054   0.3854
   8.000   1.2082   0.02462   0.01524  -0.0617   0.4012   0.3942
   8.250   1.2268   0.02508   0.01570  -0.0609   0.3968   0.4020
   8.500   1.2429   0.02563   0.01631  -0.0597   0.3918   0.4104
   8.750   1.2596   0.02618   0.01690  -0.0587   0.3870   0.4196
   9.000   1.2772   0.02672   0.01743  -0.0578   0.3824   0.4325
   9.250   1.2989   0.02717   0.01809  -0.0580   0.3785   0.5219
   9.750   1.4473   0.02932   0.02116  -0.0815   0.3670   1.0000
  10.000   1.4616   0.02994   0.02175  -0.0800   0.3634   1.0000
  10.250   1.4733   0.03069   0.02258  -0.0782   0.3596   1.0000
  10.500   1.4839   0.03151   0.02347  -0.0764   0.3556   1.0000
  10.750   1.4942   0.03235   0.02434  -0.0746   0.3511   1.0000
  11.000   1.5051   0.03316   0.02515  -0.0729   0.3470   1.0000
  11.250   1.5155   0.03405   0.02607  -0.0712   0.3430   1.0000
  11.500   1.5243   0.03506   0.02719  -0.0694   0.3388   1.0000
  11.750   1.5326   0.03610   0.02829  -0.0676   0.3345   1.0000
  12.000   1.5425   0.03707   0.02929  -0.0660   0.3307   1.0000
  12.250   1.5515   0.03811   0.03034  -0.0643   0.3265   1.0000
  12.500   1.5578   0.03940   0.03177  -0.0626   0.3222   1.0000
  12.750   1.5630   0.04077   0.03322  -0.0608   0.3171   1.0000
  13.000   1.5685   0.04213   0.03458  -0.0591   0.3119   1.0000
  13.250   1.5731   0.04365   0.03620  -0.0575   0.3070   1.0000
  13.500   1.5759   0.04536   0.03801  -0.0558   0.3013   1.0000
  13.750   1.5779   0.04714   0.03981  -0.0541   0.2952   1.0000
  14.000   1.5807   0.04897   0.04174  -0.0527   0.2901   1.0000
  14.250   1.5813   0.05107   0.04393  -0.0513   0.2837   1.0000
  14.500   1.5799   0.05335   0.04624  -0.0498   0.2764   1.0000
  14.750   1.5795   0.05570   0.04872  -0.0486   0.2695   1.0000
  15.000   1.5750   0.05843   0.05146  -0.0473   0.2611   1.0000
  15.250   1.5697   0.06140   0.05452  -0.0462   0.2512   1.0000
  15.500   1.5628   0.06456   0.05771  -0.0451   0.2406   1.0000
  15.750   1.5544   0.06794   0.06111  -0.0441   0.2299   1.0000
  16.000   1.5428   0.07172   0.06490  -0.0432   0.2178   1.0000
  16.250   1.5325   0.07544   0.06864  -0.0424   0.2068   1.0000
  16.500   1.5222   0.07922   0.07243  -0.0417   0.1978   1.0000
  16.750   1.5075   0.08360   0.07680  -0.0411   0.1887   1.0000
  17.000   1.4985   0.08736   0.08060  -0.0407   0.1814   1.0000
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